Journal articles on the topic 'Aircraft engine performance'
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1
A., Armaan, and Srinivas G. "In Tune with Times: Recent Developments in Theoretical, Experimental and Numerical techniques of Aircraft Engines." International Journal of Engineering & Technology 7, no. 2 (May 23, 2018): 805. http://dx.doi.org/10.14419/ijet.v7i2.10910.
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Today the aircraft engine designing and development work is increasing drastically. Especially aircraft engines play a vital role in order to decide the aircrafts speed and its performance. Broadly turbojet, turboprop, turbo shaft and turbofan engines comes under the category of air breathing engines. Every engine has its own purpose and application. But modern aircrafts require much more advancements. Designing a new aircraft engine has been a really challenging task to the researchers. But giving a complete holistic view of aircraft engines and research gap would definitely help a lot to the new designers. Once identified the drawbacks of engine performance can be corrected in the future. For any new design of aircraft engine researchers are suggested to take Theoretical, Experimental and Numerical approaches. Therefore present paper makes an effort to review complete recent Theoretical, Experimental and Numerical approaches which are followed till date. Under all the three approaches all the air breathing engines have been clearly explained and solicited. The effort is to identify the gaps between different approaches which are hampering the process of engine development. The paper also gives the research gaps that need to be incorporated for effective performance enhancement of the aircraft engines for aeromechanical features.
2
Chen, Min, Zihao Jia, Hailong Tang, Yi Xiao, Yonghang Yang, and Feijia Yin. "Research on Simulation and Performance Optimization of Mach 4 Civil Aircraft Propulsion Concept." International Journal of Aerospace Engineering 2019 (January 14, 2019): 1–19. http://dx.doi.org/10.1155/2019/2918646.
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Supersonic civil aircraft is of a promising area in the development of future civil transport, and aircraft propulsion system is one of the key issues which determine the success of the aircraft. To get a good conceptual design and performance investigation of the supersonic civil aircraft engine, in this article, a fast, versatile as well as trust-worthy numerical simulation platform was established to analyze the Mach 4 turbine-based combined cycle (TBCC) engine concept so as to be applied to the supersonic civil aircraft. First, a quick and accurate task requirement analysis module was newly established to analyze the mission requirement of the Mach 4 supersonic civil aircraft. Second, the TBCC engine performance simulation model was briefly presented and the number of engines on the supersonic civil aircraft was analyzed, considering single engine inoperative. Third, the Stone model and the DLR method were investigated to estimate the engine jet noise and the NOx emission of the Mach 4 supersonic civil aircraft. Finally, a multiobjective optimization tool made up of a response surface method and a genetic algorithm was developed to optimize the design parameters and the control law of the TBCC engine, in order to make the Mach 4 supersonic civil aircraft engine with better performance, lower noise, and lower emissions. The uniqueness of the developed analysis tool lies in that it affords a numerical simulation platform capable of investigating the task requirement analysis module of the supersonic civil aircraft, engine jet noise prediction model, and the NOx emission prediction model, as well as a multiobjective performance optimization tool, which is beneficial for the conceptual design and performance research of Mach 4 supersonic civil aircraft’s propulsion system.
3
Улитенко, Ю. А. "ВІДНОСНИЙ КРИТЕРІЙ ЕФЕКТИВНОСТІ ВИСОКОШВИД-КІСНОГО ЛІТАЛЬНОГО АПАРАТА." Open Information and Computer Integrated Technologies, no. 85 (July 29, 2019): 151–66. http://dx.doi.org/10.32620/oikit.2019.85.09.
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Development of perspective high-speed aircrafts inseparably linked with level of aircraft propulsion engineering as engine performances to determine aircraft capabilities as a whole. The basic requirements to engines of high-speed aircrafts are increase speed and flight height. With each new generation of turbojet bypass engine with afterburner their specific thrust and a specific impulse are increase, also application of high technologies raises leads to substantial growth of the engine cost too. At the same time existing engines design has the big reserves for modernization. For a quantitative assessment of the degree of influence of the new technical solution on the quality of the task performance by the aviation complex, criteria (indicators) of efficiency are used. However, it is not possible to find a direct functional dependence of the overall criterion of the effectiveness of the aviation complex on the technical and operational characteristics, conditions of use of a high-speed aircraft. The purpose of this work is to develop a methodology for determining the economic criterion for assessing the degree of influence of a new technical solution on the quality of the task performance by the aviation complex (the value of the integrated performance criterion). The text of the paper provides an analysis of recent research and publications. The developed relative criterion of the efficiency of a high-speed aircraft makes it possible to accomplish the goal set, as well as to estimate the costs at the cost of which the final result is achieved. It is shown that boosting engines with water injection has some advantage over other options for increasing the thrust of high-speed aircraft engines. The application of the obtained results can be used to substantiate new technical solutions and establish their impact on the quality of the task performance by the aviation complex, as well as reduce the time to create competitive high-speed aircraft.
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Zhou, Hong, Zhan Xue Wang, and Xiao Bo Zhang. "Areo-Engine Cycle Parametric Analysis and Installed Performance Calculation Based on Aircraft Flight Mission." Applied Mechanics and Materials 482 (December 2013): 277–81. http://dx.doi.org/10.4028/www.scientific.net/amm.482.277.
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The aircraft/engine integration design numerical simulation model was established. The engine design performance specifications were obtained by calculating aircraft lift-drag characteristics, mission analysis, constraint analysis. Combining engine cycle parametric analysis with installation loss computing, the engine performance parameters can be found, which meet the aircraft flight envelope performance requirements. Taking double bypass variable cycle engine as an example to check the model, the results show that the variable cycle engine can meet aircrafts thrust and fuel consumption demands under different operating conditions, and achieve cruise thrust adjustment at the same inlet mass flow to reduce installation losses.
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Sabaruddin, Ainul Aniyah, Surjatin Wiriadidjaja, Dayang Laila Abang Abdul Majid, Harijono Djojodihardjo, and Mohamed Tarmizi Ahmad. "An Investigation on the Effect of Variable Valve Timing on Piston Engine for Lightweight Aircraft." Applied Mechanics and Materials 225 (November 2012): 245–49. http://dx.doi.org/10.4028/www.scientific.net/amm.225.245.
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As the Lycoming engine had failed its attempt on using variable valve timing for aircraft piston engine back in 1940s, the idea of the technology was abandoned as the turbines were then introduced in the aviation for better performance and greater power. Since piston engines produce smaller power efficiently in the low speed than turbine engines, they are presently still practically used in most of lightweight aircraft. With the use of a variable valve timing mechanism, it may help to increase the amount of air inlet and to provide more power output with lesser fuel consumption. With the use of this new valve system, improvements in the performance of automobile engines have been recorded. The indicated improvements, however, are limited to automobile engines running with high revolutions only. Engine simulation program was run in this investigation as an attempt to predict engine performances that are appropriate for lightweight aircraft.
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Tovkach, Serhii. "CUDA-інтеграція контурів керування авіаційного газотурбінного двигуна." Aerospace Technic and Technology, no. 6 (November 27, 2023): 31–39. http://dx.doi.org/10.32620/aktt.2022.6.04.
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The problem of accelerating the process of designing aircraft gas turbine engines and their control systems, the system "AIRCRAFT-AVIATION ENGINE-FUEL", and forming the technical type of an aircraft engine, adapting to new operating conditions within the framework of experimental design bureaus (EDB) and the industry is using automated systems with low computing performance and incomplete description. Information technologies for developing engines allow duplication and mismatch of data, loss of information and time during transmission and processing for making parametric and structural decisions. To better adaptation of the characteristics of an aviation engine (AE) to the tasks solved by an aircraft in flight, it is necessary to integrate control systems. Integrated control systems are especially effective for managing today's multi-mode aircraft. On the basis of their control, optimal control programs for the power plant (PP) are formed using the criteria for evaluating the effectiveness of the aircraft. This article proposes a paradigm for building integrated control loops for an aircraft gas turbine engine, which can be formed by automating control processes, an automatic control system, and combined control programs. The objective of this research is the processes of constructing adaptive control loops for aircraft gas turbine engines. The subject of this study is the adaptive control of aircraft gas turbine engines using embedded control loops and CUDA architecture. The goal is to improve the dynamic characteristics of an aircraft gas turbine engine through adaptive control using control loops, considering various aircraft flight modes and engine operating modes. Objectives: to determine the main controllable elements of an aircraft engine, adjustable parameters and factors for constructing control loops according to the principle of adaptation; describe the mechanism of joint management of gas turbine engines; to study the processes of building an integration circuit "aircraft - power plant" and develop the concept of an integrated ACS; define the CUDA paradigm for parallel computing of control loops. Conclusions. The scientific novelty lies in the formation of a paradigm for developing adaptive control models for gas turbine engines, considering different aircraft flight modes and engine operation modes.
7
Улитенко, Юрий Александрович. "АНАЛИЗ ХАРАКТЕРИСТИК ТУРБОРЕАКТИВНОГО ДВУХКОНТУРНОГО ДВИГАТЕЛЯ С ФОРСАЖНОЙ КАМЕРОЙ СГОРАНИЯ С ВПРЫСКОМ ВОДЫ ЗА ВХОДНЫМ УСТРОЙСТВОМ." Aerospace technic and technology, no. 1 (March 7, 2019): 29–38. http://dx.doi.org/10.32620/aktt.2019.1.03.
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Development of perspective high-speed aircraft inseparably depends on the level of aircraft propulsion engineering as engine performances to determine aircraft capabilities as a whole. The basic requirements to engines of high-speed aircraft are increase speed and flight height. The new generation of turbojet bypass engine with afterburner each their specific thrust and a specific impulse increases, also the application of high technologies raises leads to substantial growth of the engine cost too. At the same time, existing engines design has big reserves for modernization. The system of water injection to the input at the turbojet bypass engine with afterburner is one of the accessible ways for design improvement. Those advanced engines theoretically will allow to satisfy requirements from designers of high-speed aircraft concerning to thrust and other key parameters, at the same time to secure continuity of already existing types of power-plants. The possibility of range extension of turbojet bypass engine with classical scheme afterburner operation till Mach number 3 is considered in this article. The analysis of existing developments is carried out. Impact of water injection to the input at turbojet bypass engine with afterburner on its performance is investigated. Results of calculations for the influence of water injection to reaction mass parameters on the engine duct and its thrust characteristics are proved. Received results will allow to increase thermodynamic efficiency and to expand range extension of turbojet bypass engine with afterburner provided to use materials that applied in aviation manufacture, as well as to reduce terms of development competitive engines for high-speed aircraft at the expense of purposeful search of their rational thermodynamic and is constructive-geometrical architecture.
8
Wang, Hao Xiang, and Hong Sen Yan. "An Adaptive Assembly Scheduling Approach in Knowledgeable Manufacturing." Applied Mechanics and Materials 433-435 (October 2013): 2347–50. http://dx.doi.org/10.4028/www.scientific.net/amm.433-435.2347.
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To address the uncertainty of production environment in aircraft engine assembly, an adaptive optimization scheduling algorithm is designed for an aircraft engine assembly line in knowledgeable manufacturing. A Q-learning adaptive scheduling model of aircraft engine assembly is built on the objective function of minimizing earliness penalty. Simulation experiments indicate that the proposed algorithm outperforms other scheduling rules much. Especially, better results are generally achieved with the increase in number of engines to show good adaptive performance.
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Grabowski, Łukasz, Konrad Pietrykowski, and Paweł Karpiński. "Energetic Analysis of the Aircraft Diesel Engine." MATEC Web of Conferences 252 (2019): 05012. http://dx.doi.org/10.1051/matecconf/201925205012.
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The analysis of the distribution of thermal energy generated during the combustion process in internal combustion engines and the estimation of individual losses are important regarding performance and efficiency. The article analyses the energy balance of the designed two-stroke opposed piston diesel engines with offset, i.e. the angle by which the crankshaft at the side of exhaust ports is ahead of the crankshaft at the side of intake ports. Based on the developed zero-dimensional engine model, a series of simulations were performed in steady-state conditions using the AVL BOOST software. The values of individual energy losses, including cooling losses, exhaust gas losses, friction losses were obtained. The influence of decreasing and increasing the offset on the performance of the tested engine was analysed.
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Azami, Muhammad Hanafi, and Mark Savill. "Comparative study of alternative biofuels on aircraft engine performance." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, no. 8 (June 22, 2016): 1509–21. http://dx.doi.org/10.1177/0954410016654506.
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Aviation industries are vulnerable to the energy crisis and simultaneously posed environmental concerns. Proposed engine technology advancements could reduce the environmental impact and energy consumption. Substituting the source of jet fuel from fossil-based fuel to biomass-based fuel will help reduce emissions and minimize the energy crisis. The present paper addresses the analysis of aircraft engine performance in terms of thrust, fuel flow and specific fuel consumption at different mixing ratio percentages (20%, 40%, 50%, 60% and 80%) of alternative biofuel blends already used in flight test (Algae biofuel, Camelina biofuel and Jatropha biofuel) at different flight conditions. In-house computer software codes, PYTHIA and TURBOMATCH, were used for the analysis and modeling of a three-shaft high-bypass-ratio engine which is similar to RB211-524. The engine model was verified and validated with open literature found in the test program of bio-synthetic paraffinic kerosene in commercial aircraft. The results indicated that lower heating value had a significant influence on thrust, fuel flow and specific fuel consumption at every flight condition and at all mixing ratio percentages. Wide lower heating value differences between two fuels give a large variation on the engine performances. Blended Kerosene–Jatropha biofuel and Kerosene–Camelina biofuel showed an improvement on gross thrust, net thrust, reduction of fuel flow and specific fuel consumption at every mixing ratio percentage and at different flight conditions. Moreover, the pure alternative of Jatropha biofuel and Camelina biofuel gave much better engine performances. This was not the case for the Kerosene–Algae blended biofuel. This study is a crucial step in understanding the influence of different blended alternative biofuels on the performance of aircraft engines.
11
Ma, Jian, Hua Su, Wan-lin Zhao, and Bin Liu. "Predicting the Remaining Useful Life of an Aircraft Engine Using a Stacked Sparse Autoencoder with Multilayer Self-Learning." Complexity 2018 (July 30, 2018): 1–13. http://dx.doi.org/10.1155/2018/3813029.
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Because they are key components of aircraft, improving the safety, reliability and economy of engines is crucial. To ensure flight safety and reduce the cost of maintenance during aircraft engine operation, a prognostics and health management system that focuses on fault diagnosis, health assessment, and life prediction is introduced to solve the problems. Predicting the remaining useful life (RUL) is the most important information for making decisions about aircraft engine operation and maintenance, and it relies largely on the selection of performance degradation features. The choice of such features is highly significant, but there are some weaknesses in the current algorithm for RUL prediction, notably, the inability to obtain tendencies from the data. Especially with aircraft engines, extracting useful degradation features from multisensor data with complex correlations is a key technical problem that has hindered the implementation of degradation assessment. To solve these problems, deep learning has been proposed in recent years to exploit multiple layers of nonlinear information processing for unsupervised self-learning of features. This paper presents a deep learning approach to predict the RUL of an aircraft engine based on a stacked sparse autoencoder and logistic regression. The stacked sparse autoencoder is used to automatically extract performance degradation features from multiple sensors on the aircraft engine and to fuse multiple features through multilayer self-learning. Logistic regression is used to predict the remaining useful life. However, the hyperparameters of the deep learning, which significantly impact the feature extraction and prediction performance, are determined based on expert experience in most cases. The grid search method is introduced in this paper to optimize the hyperparameters of the proposed aircraft engine RUL prediction model. An application of this method of predicting the RUL of an aircraft engine with a benchmark dataset is employed to demonstrate the effectiveness of the proposed approach.
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BERBENTE, Sorin, Irina-Carmen ANDREI, Gabriela STROE, and Mihaela-Luminita COSTEA. "Topical Issues in Aircraft Health Management with Applications to Jet Engines." INCAS BULLETIN 12, no. 1 (March 1, 2020): 13–26. http://dx.doi.org/10.13111/2066-8201.2020.12.1.2.
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Aircraft Health Management Technology for jet engines represents a very important problem, since it develops a large impact on reducing the engine life cycle costs, improving the fuel efficiency, increasing the engines durability and life cycle. This technology is high-end and, in order to enable an improved level of performance that far exceeds the current one, propulsion systems must comply with terms of reducing harmful emissions, maximizing fuel efficiency and minimizing noise, while improving system’s affordability and safety. Aircraft Health Management Technology includes multiple goals of aircraft propulsion control, diagnostics problems, prognostics realized, and their proper integration in control systems. Modern control for Aircraft Health Management Technology is based on improved control techniques and therefore provides improved aircraft propulsion system performances. The study presented in this paper approaches a new concept, of attractive interest currently, that is the intelligent control; in this context, the Health Management of jet engines is crucial, being focused on engine controllers which are designed to match certain operability and performance constraints. Automated Engine Health Management has the capacity to significantly reduce the maintenance effort and propulsion systems’ logistical footprint. In order to prioritize and resolve problems in the field of support engineering there are required more detailed data on equipment reliability and failures detection and management; the equipment design, operations and maintenance procedures and tooling are also very important.
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Lister, A. "II — A. Lister." Journal of Navigation 38, no. 3 (September 1985): 431–35. http://dx.doi.org/10.1017/s0373463300032793.
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Several years ago, when Airbus Industrie launched their twin-engined A 300 Airbus, it became apparent that a new generation of long-range aircraft was about to add a different facet to the shape of international air travel. The enormous power available from the big fan engines coming into use meant that adequate performance was available even when an engine failure meant the loss of half the installed thrust. Coupled to this was a standard of fuel economy and tank capacity which meant that the new aircraft were capable of operating over ranges far in excess of those previously attained by twin-engined aircraft.
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Pawlak, Małgorzata, and Michał Kuźniar. "Determination of CO2 Emissions for Selected Flight Parameters of a Business Jet Aircraft." Journal of KONES 26, no. 3 (September 1, 2019): 155–63. http://dx.doi.org/10.2478/kones-2019-0069.
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Abstract In the last two decades, there has been observed a noticeable increase in the popularity and availability of air transport services, including regional ones. This intensive development of transport is accompanied by an increase in the adverse impact to the environment, increases noise level, and exhausts emissions, despite the modification and modernization of engines. Determining the emission for regional flights takes into account the specificity of the aircrafts design, such as the size of the aircraft and the performance of the engines. In this article, an attempt was made to determine the CO2 emissions of a business jet flying from Gdansk to Rzeszow. The methodology of the research (the method of calculating emissions based on fuel consumption) and the performance characteristics of the aircraft engines have been described. In the first part of the article, the speed-altitude characteristics of the DGEN-380 engine for different cruise parameters were determined using the virtual engine test bench WESTT CS/B. These characteristics have enabled the engine to match the flight characteristics (altitude, speed). For specific flight parameters, the thrust and fuel consumption were determined. On this basis, for the adopted trajectory and flight time of an aircraft equipped with two DGEN-380 engines, total fuel consumption and CO2 emission factors and values in CRUISE phase was determined with regard to the wind speed and direction. The obtained results were illustrated graphically and discussed.
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Gloeckner, Peter, and W. Sebald. "A New Method of Calculating the Attainable Life and Reliability in Aerospace Bearings." European Journal of Engineering Research and Science 5, no. 6 (June 30, 2020): 745–50. http://dx.doi.org/10.24018/ejers.2020.5.6.1977.
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The aviation industry made significant progress improving reliability, efficiency and performance throughout the last decades. Especially aircraft engines and helicopter transmission systems contributed significantly to these improvements. The kerosene consumption decreased by 70 % and the CO2 emissions due to air transport decreased by 30 % per passenger kilometer within the last 20 years. Simultaneously, the flight safety was increased with aircraft engine in-flight-shut-downs as low as 1 ppm and „unscheduled engine removals” as low as 4 ppm. Flight safety is equal to the reliability of the systems in service. Failure of these systems directly leads to exposure of human life. Among the most critical aviation systems are aircraft engines including the rolling element bearings which support the rotors. A serious damage to the aircraft engine main shaft bearings during flight requires shout-down of the engine to avoid a further damage escalation subsequently leading to engine fire. Today, it is a requirement for aircraft to operate with one engine shut down. However, each in-flight-engine-shut-down typically is connected with flight diversion or abort and immediate landing. Inflight-shut-downs translate into increased risk for passengers and crew and substantial on cost. Therefore, rolling element bearings for aircraft engines are developed – similar to other aircraft engine components – targeting a reliability of nearly 100 % over an operation time of more than 10 000 hours prior to overhaul. To achieve this requirement despite the extreme operating conditions such as high speed and temperatures occurring in gas turbines, special high-performance materials are used for the rolling bearing components which are partially integrated in surrounding engine parts like shafts and housings. These special conditions - deviating from conventional industrial rolling element bearing applications - are currently not sufficiently considered in the standardized method of calculating the bearing life per ISO 281. A new method of calculating the attainable life of rolling elements bearing in aerospace applications is presented. This method considers the special aerospace conditions and materials and thus enables a higher reliability of the theoretical analysis and life prediction.
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Gloeckner, Peter, and W. Sebald. "New Method of Calculating the Attainable Life and Reliability in Aerospace Bearings." European Journal of Engineering and Technology Research 5, no. 6 (June 30, 2020): 745–50. http://dx.doi.org/10.24018/ejeng.2020.5.6.1977.
Full textAbstract:
The aviation industry made significant progress improving reliability, efficiency and performance throughout the last decades. Especially aircraft engines and helicopter transmission systems contributed significantly to these improvements. The kerosene consumption decreased by 70 % and the CO2 emissions due to air transport decreased by 30 % per passenger kilometer within the last 20 years. Simultaneously, the flight safety was increased with aircraft engine in-flight-shut-downs as low as 1 ppm and „unscheduled engine removals” as low as 4 ppm. Flight safety is equal to the reliability of the systems in service. Failure of these systems directly leads to exposure of human life. Among the most critical aviation systems are aircraft engines including the rolling element bearings which support the rotors. A serious damage to the aircraft engine main shaft bearings during flight requires shout-down of the engine to avoid a further damage escalation subsequently leading to engine fire. Today, it is a requirement for aircraft to operate with one engine shut down. However, each in-flight-engine-shut-down typically is connected with flight diversion or abort and immediate landing. Inflight-shut-downs translate into increased risk for passengers and crew and substantial on cost. Therefore, rolling element bearings for aircraft engines are developed – similar to other aircraft engine components – targeting a reliability of nearly 100 % over an operation time of more than 10 000 hours prior to overhaul. To achieve this requirement despite the extreme operating conditions such as high speed and temperatures occurring in gas turbines, special high-performance materials are used for the rolling bearing components which are partially integrated in surrounding engine parts like shafts and housings. These special conditions - deviating from conventional industrial rolling element bearing applications - are currently not sufficiently considered in the standardized method of calculating the bearing life per ISO 281. A new method of calculating the attainable life of rolling elements bearing in aerospace applications is presented. This method considers the special aerospace conditions and materials and thus enables a higher reliability of the theoretical analysis and life prediction.
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Brown, H., and J. A. Elgin. "Aircraft Engine Control Mode Analysis." Journal of Engineering for Gas Turbines and Power 107, no. 4 (October 1, 1985): 838–44. http://dx.doi.org/10.1115/1.3239820.
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This paper describes the control mode analysis procedure that is used to establish closed-loop control requirements for advanced aircraft propulsion systems. The procedure utilizes anticipated variations in engine component performance, engine deterioration, and control tolerances in a statistical analysis to establish corresponding variations in engine output performance and safety parameters. Potential closed-loop control configurations are evaluated by this process, compared, and the best configuration selected for implementation into control law and schedule designs. A byproduct of the analysis is the establishment of engine design and performance margins. The paper will describe typical engine variational models used in this process, the General Electric COMET program designed to automate the analysis, and typical mode study results based on a current augmented turbofan engine.
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Zellner, B., W. Sterr, and O. Herrmann. "Integration of Turbo-Expander and Turbo-Ramjet Engines in Hypersonic Vehicles." Journal of Engineering for Gas Turbines and Power 116, no. 1 (January 1, 1994): 90–97. http://dx.doi.org/10.1115/1.2906815.
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Turbo-expander-ramjet and turbo-ramjet are two engine concepts considered for hypersonic aircraft designs with a flight regime between Mach 0 and 7. To establish any performance or integration aspects for these two combined-cycle engine types, an extended study of a variety of influence parameters is necessary, because the interaction between aircraft and propulsion system is even stronger than on conventional aircraft. In fact, the propulsion system is very sensitive to intake and nozzle/afterbody design at these high speeds. This paper presents the engine configurations chosen for comparison and describes the computer program used for the propulsion system performance simulation, including all relevant integration aspects. Furthermore, some results of propulsion system performance for a generic hypersonic aircraft and a typical ascent profile will be compared to indicate the special characteristics of the engines. Finally, some thoughts concerning the suitability and relevant technological requirements of the two engine types—seen from an aircraft manufacturer’s view—are included. The paper includes the results of two diploma theses, written by W. Sterr [1] and B. Zellner [2] at the Technical University of Munich, supervised by Prof. H. Rick (LFA) and O. Herrmann (MBB).
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Kolden, J. J. "A Method of Sizing Multi-Cycle Engines for Hypersonic Aircraft." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 217–22. http://dx.doi.org/10.1115/1.2906165.
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A method of sizing multi-cycle engines for integration with hypersonic vehicles has been developed. The new procedure independently sizes the inlet, each engine cycle, and the nozzle during the vehicle sizing loop to optimize propulsion/aircraft integration. Using uninstalled engine performance for each cycle of a multi-cycle engine along with inlet and nozzle performance and an estimate of aircraft drag, an iterative procedure is utilized to size each component simultaneously. A propulsion system is defined that meets the aircraft thrust requirements at all mission points. The inlet is sized to provide airflow such that the maximum Mach cruise and/or combat thrust conditions are met. Each cycle is sized independently to meet all thrust requirements while minimizing either inlet drag or engine size. Nozzle sizing must trade off thrust, drag and nozzle weight. This methodology has been incorporated into a computer code entitled “Multi-Cycle Engine Sizing Program,” MCESP.
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Naeem, M., R. Singh, and D. Probert. "Impacts of aero-engine deteriorations on military aircraft mission's effectiveness." Aeronautical Journal 105, no. 1054 (December 2001): 685–96. http://dx.doi.org/10.1017/s0001924000012768.
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Abstract International political and socio-economic developments have led the armed forces of many countries to become more aware of how their increasingly-stringent financial budgets are spent. One major expenditure for military authorities is upon aero-engines, because in-service deterioration in any mechanical device, such as an aircraft's gas-turbine engine, is inevitable. Each deterioration has an adverse effect on the performance and shortens the reliable operational life of the engine, thereby resulting in higher life-cycle costs. For a military aircraft's mission-profiles, the consequences of an aero-engine's deterioration upon the aircraft's operational-effectiveness as well as its fuel consumption and life have been predicted in this project using validated computer-simulations. These help in making wiser management-decisions, so leading to the achievement of improved engine utilisation, lower overall life-cycle costs and optimal mission effectiveness for squadrons of aircraft.
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Yildirim, Mustagime Tülin, and Bülent Kurt. "Aircraft Gas Turbine Engine Health Monitoring System by Real Flight Data." International Journal of Aerospace Engineering 2018 (2018): 1–12. http://dx.doi.org/10.1155/2018/9570873.
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Modern condition monitoring-based methods are used to reduce maintenance costs, increase aircraft safety, and reduce fuel consumption. In the literature, parameters such as engine fan speeds, vibration, oil pressure, oil temperature, exhaust gas temperature (EGT), and fuel flow are used to determine performance deterioration in gas turbine engines. In this study, a new model was developed to get information about the gas turbine engine’s condition. For this model, multiple regression analysis was carried out to determine the effect of the flight parameters on the EGT parameter and the artificial neural network (ANN) method was used in the identification of EGT parameter. At the end of the study, a network that predicts the EGT parameter with the smallest margin of error has been developed. An interface for instant monitoring of the status of the aircraft engine has been designed in MATLAB Simulink. Any performance degradation that may occur in the aircraft’s gas turbine engine can be easily detected graphically or by the engine performance deterioration value. Also, it has been indicated that it could be a new indicator that informs the pilots in the event of a fault in the sensor of the EGT parameter that they monitor while flying.
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Cue, R. W., and D. E. Muir. "Engine Performance Monitoring and Troubleshooting Techniques for the CF-18 Aircraft." Journal of Engineering for Gas Turbines and Power 113, no. 1 (January 1, 1991): 11–19. http://dx.doi.org/10.1115/1.2906519.
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The F404-GE-400 engines of the CF-18 aircraft are the first engines of the Canadian Forces to be maintained under a formal on-condition maintenance program. In support of this program, the Canadian Forces are developing advanced troubleshooting and performance monitoring procedures based on information recorded by the aircraft In-flight Engine Condition Monitoring System (IECMS). A suite of computer programs has been developed that enables maintenance personnel to access, display, and analyze in-flight event data recorded by the IECMS and to track the performance of individual engines based on “health indices” derived from the IECMS take-off ground roll recordings. The new techniques have been under evaluation at each of the CF-18 main operating bases for a period of approximately 14 months. Results to date indicate that the IECMS recordings provide a considerable amount of information of benefit to engine technicians and maintenance planners.
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Smith, R. H., J. D. Chisholm, and J. F. Stewart. "Optimizing Aircraft Performance With Adaptive, Integrated Flight/Propulsion Control." Journal of Engineering for Gas Turbines and Power 113, no. 1 (January 1, 1991): 87–94. http://dx.doi.org/10.1115/1.2906535.
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An adaptive, integrated flight/propulsion control algorithm called Performance Seeking Control (PSC) has been developed to optimize total aircraft performance during steady-state engine operation. The multimode algorithm will minimize fuel consumption at cruise conditions; maximize excess thrust (thrust minus drag) during aircraft accelerations, climbs, and dashes; and extend engine life by reducing Fan Turbine Inlet Temperature (FTIT) when the extended life mode is engaged. On-board models of the inlet, engine, and nozzle are optimized to compute a set of control trims, which are then applied as increments to the nominal engine and inlet control schedules. The on-board engine model is continually updated to match the operating characteristics of the actual engine cycle through the use of a Kalman filter, which accounts for anomalous engine operation. The PSC algorithm will be flight demonstrated on an F-15 test aircraft under the direction of the NASA Ames/Dryden Flight Research Facility. This paper discusses the PSC design strategy, describes the control algorithm, and presents results from high-fidelity, nonlinear aircraft/engine simulations. Simulation results indicate that thrust increases as high as 15 percent and specific fuel consumption reductions up to 3 percent are realizable by the PSC system.
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Ntantis, E. L., and P. N. Botsaris. "Diagnostic Methods for an Aircraft Engine Performance." Journal of Engineering Science and Technology Review 8, no. 4 (August 2015): 64–72. http://dx.doi.org/10.25103/jestr.084.10.
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Rosell, Daniel, and Tomas Grönstedt. "Design Considerations of Low Bypass Ratio Mixed Flow Turbofan Engines with Large Power Extraction." Fluids 7, no. 1 (January 1, 2022): 21. http://dx.doi.org/10.3390/fluids7010021.
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The possibility of extracting large amounts of electrical power from turbofan engines is becoming increasingly desirable from an aircraft perspective. The power consumption of a future fighter aircraft is expected to be much higher than today’s fighter aircraft. Previous work in this area has concentrated on the study of power extraction for high bypass ratio engines. This motivates a thorough investigation of the potential and limitations with regards to performance of a low bypass ratio mixed flow turbofan engine. A low bypass ratio mixed flow turbofan engine was modeled, and key parts of a fighter mission were simulated. The investigation shows how power extraction from the high-pressure turbine affects performance of a military engine in different parts of a mission within the flight envelope. An important conclusion from the analysis is that large amounts of power can be extracted from the turbofan engine at high power settings without causing too much penalty on thrust and specific fuel consumption, if specific operating conditions are fulfilled. If the engine is operating (i) at, or near its maximum overall pressure ratio but (ii) further away from its maximum turbine inlet temperature limit, the detrimental effect of power extraction on engine thrust and thrust specific fuel consumption will be limited. On the other hand, if the engine is already operating at its maximum turbine inlet temperature, power extraction from the high-pressure shaft will result in a considerable thrust reduction. The results presented will support the analysis and interpretation of fighter mission optimization and cycle design for future fighter engines aimed for large power extraction. The results are also important with regards to aircraft design, or more specifically, in deciding on the best energy source for power consumers of the aircraft.
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Murat Otkur. "Altitude Performance and Fuel Consumption Modelling of Aircraft Piston Engine Rotax 912 S/ULS." Journal of Advanced Research in Applied Sciences and Engineering Technology 23, no. 1 (May 14, 2021): 18–25. http://dx.doi.org/10.37934/araset.23.1.1825.
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Rotax 912 spark-ignition (SI) naturally aspirated aircraft piston engine is one of the most popular prime movers for the ultra-light weight aircrafts used for short and moderate range flights. SI engines operate at stoichiometric combustion and at high altitude conditions atmospheric pressure is lower than sea level reducing mass of air intake to the engine. At these conditions engine power degrades significantly from sea level, affecting flight parameters such as range and endurance. In order to optimize these parameters, engine power modelling is of vital importance. Within the scope of this study, a thermodynamic SI engine model with performance parameters (break torque and power) and fuel consumption estimation developed in MATLAB/Simulink software. Model tuning is realised using data extracted from Rotax engine operating manual at sea level and high altitude conditions. Model inputs are set as altitude, throttle lever and engine speed. Pressure drop at the intake port is modelled as a function of mass air flow using engine operating manual pressure data at various engine speed points. Mass air flow is determined via employing a volumetric efficiency map based on intake port pressure and engine speed inputs, calibrated using engine operating manual fuel data considering stoichiometric combustion. Compression and expansion strokes area modelled as isentropic events and combustion is modelled as constant volume heat input at top dead centre (TDC). However a combustion efficiency map based on engine speed and fuel flow is employed for the heat input in order to tune the work output of the engine and heat loss to the coolant and exhaust. Pumping loss is calculated based on friction mean effective pressure data. Introduced approach provides high accuracy performance and fuel consumption modelling based on engine operating manual data and can be used for flight parameters optimization studies.
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SZRAMA, Sławomir. "F-16 turbofan engine monitoring system." Combustion Engines 177, no. 2 (May 1, 2019): 23–35. http://dx.doi.org/10.19206/ce-2019-205.
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The multirole F-16 is the most advanced aircraft in the Polish Air Forces. It has been equipped with the very modern, sophisticated and advanced turbofan engine F100-PW-229. Due to the fact, that there is only one engine, its reliability, durability, efficiency and performance are the crucial factors for the safety reasons. In the article author researched maintenance system of the F100 turbofan engines, to describe Engine Monitoring System features. Engine Monitoring System (EMS) is the key element in the engine prognostic and health monitoring. The EMS provides engine fault indicators to the pilots and technicians and with the engine performance trending affects the F-16 flight safety risk and enhanced engine maintenance management concept. The main goal of this article was to provide information on the F-16 Engine Monitoring System and its impact on the aircraft airworthiness and F-16 fleet readiness resulting from the engine reliability. It is also an introduction to the F-16 Engine Health Management concept.
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Antonopoulos, AK, RG Papagiannakis, and DT Hountalas. "Application of a diagnostic technique for evaluating the quality of the air–fuel mixture and the ignition quality of a spark-ignition reciprocating aircraft piston engine." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 3 (December 20, 2016): 571–82. http://dx.doi.org/10.1177/0954410016683414.
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The performance characteristics of an aircraft piston engine are affected mainly by the air–fuel mixture quality (i.e. condition of the fuel injection system) and by the spark timing and spark duration (i.e. condition of ignition system). Thus, the present work focuses on investigating the effect of both fuel injection and spark ignition systems on performance characteristics of two aircraft piston engines which are of the same type but have overhauled by two different workshops. The investigation is conducted by applying an existing diagnostic technique, which is based on the simultaneous recording and processing of two electric signals: one corresponding to cylinder pressure and the second corresponding to the ignition system. The basic characteristics of the proposed methodology are simplicity and field applicability on engines of this type. A detailed experimental investigation has been conducted on the aforementioned two aircraft piston engines on a dedicated test bench. From the results, it is revealed that the proposed diagnostic methodology provides reliable information for the effect of both the ignition and fuel injection systems on engine performance characteristics. The results derived from the specific work enable the comparative evaluation of the engines and their ignition and fuel injection systems. Finally, based on this first investigation, the proposed methodology seems to be promising, because it can be easily applied on any type of spark-ignited engine and especially on aircraft piston engine, where due to its geometry and multicylinder nature, the application of lab techniques on the field is, if not impossible, extremely difficult.
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Balicki, Włodzimierz, Paweł Głowacki, Stefan Szczecinski, Ryszard Chachurski, and Jerzy Szczeciński. "Effect of the Atmosphere on the Performances of Aviation Turbine Engines." Acta Mechanica et Automatica 8, no. 2 (August 15, 2014): 70–73. http://dx.doi.org/10.2478/ama-2014-0012.
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Abstract The paper presents how the parameters defining the state of the atmosphere: pressure, temperature, humidity, are affecting performance of the aircraft turbine engines and their durability. Also negative impact of dust pollution level is considered as an important source of engine deterioration. Article highlights limitation of the aircraft takeoff weight (TOW) and requirements for length of the runways depending on weather condition changes. These problems stem from the growing “demand” of gas turbine engines for an air. The highest thrust engines have air mass flow more than 1000 kg/s. Engine inlet ice formation is presented as a result of weather conditions and inlet duct design features.
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Ismail, I. H., and F. S. Bhinder. "Simulation of Aircraft Gas Turbine Engines." Journal of Engineering for Gas Turbines and Power 113, no. 1 (January 1, 1991): 95–99. http://dx.doi.org/10.1115/1.2906536.
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The paper describes a computer program to simulate aircraft gas turbine engines. The program has been written for IBM-compatible microcomputers and is modular in its appraoch. Either analytical equations or detailed performance characteristics of individual components are used to model the steady-state operation of the complete engine.
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Henderson, R. P., J. R. R. A. Martins, and R. E. Perez. "Aircraft conceptual design for optimal environmental performance." Aeronautical Journal 116, no. 1175 (January 2012): 1–22. http://dx.doi.org/10.1017/s000192400000659x.
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Abstract Consideration of the environmental impact of aircraft has become critical in commercial aviation. The continued growth of air traffic has caused increasing demands to reduce aircraft emissions, imposing new constraints on the design and development of future airplane concepts. In this paper, an aircraft design optimisation framework is used to design aircraft that minimise specific environmental metrics. Multidisciplinary design optimisation is used to optimise aircraft by simultaneously considering airframe, engine and mission. The environmental metrics considered in this investigation are CO2 emissions — which are proportional to fuel burn — and landing-takeoff NOx emissions. The results are compared to those of an aircraft with minimum direct operating cost. The design variables considered in the optimisation problems include aircraft geometry, engine parameters, and cruise settings. An augmented Lagrangian particle swarm optimiser and a genetic algorithm are used to solve the single objective and multi-objective optimisation problems, respectively.
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Xiao, Lingfei, Min Xu, Yuhan Chen, and Yusheng Chen. "Hybrid Grey Wolf Optimization Nonlinear Model Predictive Control for Aircraft Engines Based on an Elastic BP Neural Network." Applied Sciences 9, no. 6 (March 25, 2019): 1254. http://dx.doi.org/10.3390/app9061254.
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In order to deal with control constraints and the performance optimization requirements in aircraft engines, a new nonlinear model predictive control method based on an elastic BP neural network with a hybrid grey wolf optimizer is proposed in this paper. Based on the acquired aircraft engines data, the elastic BP neural network is used to train the prediction model, and the grey wolf optimization algorithm is applied to improve the selection of initial parameters in the elastic BP neural network. The accuracy of network modeling is increased as a result. By introducing the logistics chaotic sequence, the individual optimal search mechanism, and the cross operation, the novel hybrid grey wolf optimization algorithm is proposed and then used in receding horizon optimization to ensure real-time operation. Subsequently, a nonlinear model predictive controller for aircraft engine is obtained. Simulation results show that, with constraints in the control signal, the proposed nonlinear model predictive controller can guarantee that the aircraft engine has a satisfactory performance.
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Jamil, Mohd Khairuladha, Mohd Ezwani Kadir, Mohamad Zikri Zainol, Abu Hanifah Abdullah, and Abu Zaid Bakar. "Preliminary Development of Electric Motorcycle Engine for Sport Aviation Vehicles." Applied Mechanics and Materials 225 (November 2012): 250–54. http://dx.doi.org/10.4028/www.scientific.net/amm.225.250.
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Flying activities of sport aviation vehicles normally use Internal Combustion Engines (ICE) for their powerplant, which emits Carbon Dioxide (CO2) and also produces noise. Environmental issues regarding harmful gas emission and noise may restrict the sport aviation activities and resulting in reduction of interest in flying as a sport activity. The feasible solution for this issue is by replacing the Internal Combustion Engines (ICE) with Electric Engines on all sport flying vehicles. The Modenas CTric Electric Engines was tested to measure the parameters required by comparable Internal Combustion Engine used by sport aviation flyers. Other parameters; engine endurance, temperature and performance, were also tested. The bench test was conducted using specially design test rig. The results show that there is a possibility for the Modenas CTric Motorcycles Electric Engine used as an alternate source of powerplant for paramotors and microlight aircraft. However, there is penalty on the vehicle payloads due to weight of the battery. Lighter battery technology integration is to be developed to reduce the weight of the flight vehicles. This study serves as a platform for further work in electric engine technology for commercial aircraft application. Availability of green engine (no emission and noise output) will generate more interest in sport aviation activities and prepare for the future commercial Electric Engine aircraft application.
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Henzel, Maciej, Krzysztof Falkowski, and Aleksander Olejnik. "The analysis of “more electric engine” technology to improve the environmental performance of aircraft jet engine." E3S Web of Conferences 46 (2018): 00029. http://dx.doi.org/10.1051/e3sconf/20184600029.
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In aviation, there is now a dynamic development of aircraft equipment related to the implementation of “more electric aircraft” technology. This concept offers the ability to improve the use of on-board systems, e.g. environmental operating conditions of aircraft jet engine. This technology is named “more electric engine”. It allows the use of magnetic levitation technology at engine turbine shaft bearing. The development of this technology relates to the dynamic change of electronic power systems for civilian transport aircraft, the use of adaptive control methods and new materials in aviation technology. All technologies are improved the environmental operating conditions of the on-board system, e.g. operational flexibility, technological potential growth. [1] In the paper will be presented the TS-21 aircraft jet engine. This engine is modernized in the Jet Engine Laboratory of the Military University of Technology. The paper is presented a digital engine control system, the operating parameters acquisition system and magnetic bearing system. It is described the concept of active magnetic suspension of the turbine engine shaft support. The magnetic suspension technology allows eliminate mechanical bearing arrangements with an oil installation, friction forces and classical, mechanical bearings. The paper contains the simulation and experimental results of a modernized jet engine TS-21.
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Davis, Milt, and Peter Montgomery. "A Flight Simulation Vision for Aeropropulsion Altitude Ground Test Facilities." Journal of Engineering for Gas Turbines and Power 127, no. 1 (January 1, 2005): 8–17. http://dx.doi.org/10.1115/1.1806452.
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Testing of a gas turbine engine for aircraft propulsion applications may be conducted in the actual aircraft or in a ground-test environment. Ground test facilities simulate flight conditions by providing airflow at pressures and temperatures experienced during flight. Flight-testing of the full aircraft system provides the best means of obtaining the exact environment that the propulsion system must operate in but must deal with limitations in the amount and type of instrumentation that can be put on-board the aircraft. Due to this limitation, engine performance may not be fully characterized. On the other hand, ground-test simulation provides the ability to enhance the instrumentation set such that engine performance can be fully quantified. However, the current ground-test methodology only simulates the flight environment thus placing limitations on obtaining system performance in the real environment. Generally, a combination of ground and flight tests is necessary to quantify the propulsion system performance over the entire envelop of aircraft operation. To alleviate some of the dependence on flight-testing to obtain engine performance during maneuvers or transients that are not currently done during ground testing, a planned enhancement to ground-test facilities was investigated and reported in this paper that will allow certain categories of flight maneuvers to be conducted. Ground-test facility performance is simulated via a numerical model that duplicates the current facility capabilities and with proper modifications represents planned improvements that allow certain aircraft maneuvers. The vision presented in this paper includes using an aircraft simulator that uses pilot inputs to maneuver the aircraft engine. The aircraft simulator then drives the facility to provide the correct engine environmental conditions represented by the flight maneuver.
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Zanini, Nicola, Alessio Suman, Riccardo Friso, and Michele Pinelli. "Analysis of satellite-derived data for the study of fouling in aircraft engines." Journal of Physics: Conference Series 2385, no. 1 (December 1, 2022): 012134. http://dx.doi.org/10.1088/1742-6596/2385/1/012134.
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Abstract Atmospheric particulate is one of the main causes of performance degradation in gas turbine engines, especially in the aeronautical field where filter barriers are absent. The ingested particles can stick to the blade surfaces of the engine, varying their shape and roughness. As a consequence, engine performance degradation takes place. The type and the amount of the particles ingested depend on the flight zones and altitude. During their missions, aircrafts follow a prescribed path defined in terms of altitude, longitude, and latitude. During its route, the aircraft engine encounters different environments characterized by different temperature, pressure, and air composition. Regarding the latter issue, the knowledge of this characteristic can be key information when these statistics are needed for obtaining data useful for engine degradation assessment or prediction. Many satellites, such as the environmental satellite CALIPSO, are employed to study the terrestrial aerosol and clouds profile by using a LIDAR (Laser Detection and Ranging). This technology is commonly used to determine the distance between a light emitter and an object and it is based on the light refraction phenomenon. Backscatter coefficients profiles data, which characterize the distribution of particles and aerosols in the atmosphere, are available in the open literature from the findings of CALIPSO. In this work, a new methodology to estimate the aerosol type and concentration encountered by an aircraft during a mission is proposed. To test the feasibility of this method, two aircraft missions for different length scales (medium and long haul) are analyzed and an estimate of the particulate encountered by the engines is provided. The mission analysis has been conducted by discretizing the altitude profile, longitude, and latitude coordinates of each flight and then cross-referencing them with the particulate concentration obtained from CALIPSO data.
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Grabowski, Łukasz, Ksenia Siadkowska, and Krzysztof Skiba. "Simulation Research of Aircraft Piston Engine Rotax 912." MATEC Web of Conferences 252 (2019): 05007. http://dx.doi.org/10.1051/matecconf/201925205007.
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This paper reports the results of simulation works of Rotax 912 aircraft piston engine, which is a basic unit in most ultra-light aircrafts. The method for preparing the model aircraft engine operation process was presented. Simulation tests were carried out in the AVL Boost programme. The programme allows a full use of zero-dimensional and one-dimensional modelling. It also allows a comparison of other engine models. The developed model has enabled us to simulate the flow of air through the inlet pipes, carburettors, valves and combustion process. The preparation of the model required us to enter parameters that are not available in the manufacturer's catalogue, therefore, necessary measurements and analysis of the engine parts were carried out on a laboratory bench. The calculations in the AVL Boost programme were carried out in the conditions determined for the selected BMEP values with the objective of characterising the engine performance by determining its power, torque and fuel consumption.
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Omar, H., V. S. Kuz'michev, and A. Yu Tkachenko. "Improving the efficiency of aviation turbofan engines by using an intercooler and a recuperative heat exchanger." VESTNIK of Samara University. Aerospace and Mechanical Engineering 19, no. 3 (December 30, 2020): 85–99. http://dx.doi.org/10.18287/2541-7533-2020-19-3-85-99.
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Continuous improvement of fuel efficiency of aircraft engines is the main global trend in modern engine construction. To date, aviation gas turbine engines have reached a high degree of thermodynamic and design-and technology perfection. One of the promising ways to further improve their fuel efficiency is the use of complex thermodynamic cycles with turbine exhaust heat regeneration and with intermediate cooling in the process of air compression. Until recently, the use of cycles with a recuperative heat exchanger and an intercooler in aircraft gas turbine engines was restrained by a significant increase in the mass of the power plant due to the installation of heat exchangers. Currently, it has become technologically possible to create compact, light, high-efficiency heat exchangers for use on aircraft without compromising their performance. An important target in the design of engines with heat recovery is to select the parameters of the working process that provide maximum efficiency of the aircraft system. The article focuses on the statement of the task of optimization and choice of rational parameters of the working process of a bypass three-shaft turbojet engine with an intercooler and a recuperative heat exchanger. On the basis of the developed method multi-criteria optimization was carried out by means of numerical simulations. The results of optimization of thermodynamic cycle parameters of a bypass three-shaft turbojet engine with an intercooler and a recuperative heat exchanger in the aircraft system according to such criteria as the total weight of the engine and fuel required for the flight, and the aircraft specific fuel consumption per ton - kilometer of the payload are presented. A passenger aircraft of the Airbus A310-300 type was selected. The developed mathematical model for calculating the mass of a compact heat exchanger, designed to solve optimization problems at the stage of conceptual design of the engine is presented. The developed methods and models are implemented in the ASTRA program. The possibility of improving the efficiency of turbofan engines due to the use of complex thermodynamic cycles is shown.
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Jia, Yuan, Jinye Li, and Jianghao Wu. "Power Fan Design of Blended-Wing-Body Aircraft with Distributed Propulsion System." International Journal of Aerospace Engineering 2021 (September 7, 2021): 1–18. http://dx.doi.org/10.1155/2021/5128136.
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A blended-wing-body aircraft has the advantages of high lift-to-drag ratio, low noise, and high economy compared with traditional aircraft. It is currently a solution with great potential to become a future civilian passenger aircraft. However, most airplanes with this layout use distributed power, and the power system is on the back of the fuselage, with embedded or back-supported engines. This type of design causes the boundary layer suction effect. The boundary layer ingestion (BLI) effect can fill the wake of the aircraft and improve the propulsion efficiency of the engine. However, it causes huge design difficulties, especially when the aircraft and the engine are strongly coupled. In this paper, an aircraft with a coupled engine configuration is studied. The internal and external flow fields are calculated through numerical simulation. A realistic calculation model is obtained through the coupling of boundary conditions. On the basis of the influence of the external flow on the internal flow under the coupled condition, the influence of the BLI effect on the aerodynamic performance of the fan is investigated.
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Léonard, Olivier, Sébastien Borguet, and Pierre Dewallef. "Adaptive Estimation Algorithm for Aircraft Engine Performance Monitoring." Journal of Propulsion and Power 24, no. 4 (July 2008): 763–69. http://dx.doi.org/10.2514/1.34320.
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Mazlan, Nurul Musfirah, Mark Savill, and Timos Kipouros. "Effects of biofuels properties on aircraft engine performance." Aircraft Engineering and Aerospace Technology 87, no. 5 (September 7, 2015): 437–42. http://dx.doi.org/10.1108/aeat-09-2013-0166.
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Alexiou, Alexios, Nikolaos Aretakis, Ioannis Kolias, and Konstantinos Mathioudakis. "Novel Aero-Engine Multi-Disciplinary Preliminary Design Optimization Framework Accounting for Dynamic System Operation and Aircraft Mission Performance." Aerospace 8, no. 2 (February 12, 2021): 49. http://dx.doi.org/10.3390/aerospace8020049.
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This paper presents a modular, flexible, extendable and fast-computational framework that implements a multidisciplinary, varying fidelity, multi-system approach for the conceptual and preliminary design of novel aero-engines. In its current status, the framework includes modules for multi-point steady-state engine design, aerodynamic design, engine geometry and weight, aircraft mission analysis, Nitrogen Oxide (NOx) emissions, control system design and integrated controller-engine transient-performance analysis. All the modules have been developed in the same software environment, ensuring consistent and transparent modeling while facilitating code maintainability, extendibility and integration at modeling and simulation levels. Any simulation workflow can be defined by appropriately combining the relevant modules. Different types of analysis can be specified such as sensitivity, design of experiment and optimization. Any combination of engine parameters can be selected as design variables, and multi-disciplinary requirements and constraints at different operating points in the flight envelope can be specified. The framework implementation is exemplified through the optimization of an ultra-high bypass ratio geared turbofan engine with a variable area fan nozzle, for which specific aircraft requirements and technology limits apply. Although the optimum design resulted in double-digit fuel-burn benefits compared to current technology engines, it did not meet engine-response requirements, highlighting the need to include transient-performance assessments as early as possible in the preliminary engine design phase.
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Luo, Zhicong, and Kateryna Maiorova. "DEVELOPMENT TREND OF LAGE AIRCRAFT ENGINE IN THE FUTURE." Grail of Science, no. 14-15 (June 10, 2022): 371–75. http://dx.doi.org/10.36074/grail-of-science.27.05.2022.066.
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With the rapid development of the world economy and technology, engine technology has made a series of progress in the aerospace field. However, the problems of environmental pollution and energy crisis are becoming more and more serious. The development of advanced aircraft engines can contribute to thrust-to-weight ratio, fuel consumption rate, lifetime cost, pollutant emission, safety and reliability, etc., reducing energy consumption and reducing flight costs. This paper briefly introduces the types and performance of modern advanced aero-engines, summarizes their practical applications in various aviation fields, and looks forward to the development direction of future aircraft engines.
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WYGONIK, Piotr. "Selection criteria of turbine engine parameters for multi-purpose aircraft." Combustion Engines 127, no. 4 (November 1, 2006): 19–33. http://dx.doi.org/10.19206/ce-117336.
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At the stage of a power unit selection for a multi-purpose aircraft the problem of mutual relations between the dimension of an aircraft and an engine should be solved. Starting from the motion equation of an aircraft and the theory of similarity the criteria and performance were determined which connect in a geometrical and power way the engine and the aircraft. The analysis of the influence of flight conditions and the parameters of an engine comparative cycle on the geometrical dimensions was conducted. In the paper it was shown that the fundamental flight stage which determines the relations between the geometrical parameters of the aircraft and the engine is the take-off or supersonic flight on the big altitude. Usually the parameters selection of the turbine engine thermal cycle is done on the basis of the internal characteristics of the engine, such as specific thrust and specific fuel usage. In case of the turbofan engine model with the mixer, afterburner, and the aircraft model (with simplified aerodynamic and mass characteristics) the influence of the cycle parameters on the performance and aerodynamic lift/drag ratio, the agreed range and the theoretical range was described.
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Schnell, Rainer, Xin Zhao, Efthymios Rallis, Mavroudis Kavvalos, Smruti Sahoo, Markus Schnoes, and Konstantinos Kyprianidis. "Assessment of a Turbo-Electric Aircraft Configuration with Aft-Propulsion Using Boundary Layer Ingestion." Aerospace 6, no. 12 (December 16, 2019): 134. http://dx.doi.org/10.3390/aerospace6120134.
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In this paper, a turbo-electric propulsion system was analyzed, and its performance was assessed. The aircraft considered here was a single-aisle, medium-range configuration targeting a capacity of 150 Pax. The propulsion concept comprised two boosted geared turbofan engines mounted under-wing. Those main engines were supported by an electrically driven aft-propulsor contributing to the thrust generation and by taking advantage of ingesting the boundary layer of the fuselage for potentially higher levels of propulsive efficiency and allowing for the improved operation of the main engines. The performance assessment as carried out in the context of this paper involved different levels: Firstly, based on the reference aircraft and the detailed description of its major components, the engine performance model for both main engines, as well as for the electrically driven aft-propulsor was set up. The methodology, as introduced, has already been applied in the context of hybrid-electric propulsion and allowed for the aforementioned aircraft sizing, as well as the subsequent gas turbine multi-point synthesis (simulation). A geared turbofan architecture with 2035 technology assumptions was considered for the main engine configuration. The present trade study focused on the design and performance analysis of the aft-propulsor and how it affected the performance of the main engines, due to the electric power generation. In order to allow for a more accurate description of the performance of this particular module, the enhanced streamline curvature method with an underlying and pre-optimized profile database was used to design a propulsor tailored to meet the requirements of the aft propulsor as derived from the cycle synthesis and overall aircraft specification; existing design expertise for novel and highly integrated propulsors could be taken advantage of herein. The resulting performance characteristics from the streamline curvature method were then fed back to the engine performance model in a closely coupled approach in order to have a more accurate description of the module behavior. This direct coupling allowed for enhanced sensitivity studies, monitoring different top-level parameters, such as the thrust/power split between the main engines and the aft propulsor. As a result, different propulsor specifications and fan designs with optimal performance characteristics were achieved, which in return affected the performance of all subsystems considered.
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Xu, Li, Geng Huang He, Zhao Hui Cai, Dong Kai Jia, and Zhen Bo Wang. "Research on the High-Efficiency and Energy-Saving Cutting of the Aero Engine Fan Blades." Advanced Materials Research 154-155 (October 2010): 273–77. http://dx.doi.org/10.4028/www.scientific.net/amr.154-155.273.
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As the heart of the aircraft, aircraft engine is the decisive factors of aircraft performance. The turbofan engine technology is in the forward position of aero engine, and has become the main power of fighter and civil aircraft. In order to improve the processing efficiency of the aero engine fan blades, a high-efficiency and energy-saving technology was given to replace the traditional processing methods. The paper analyzed and researched the problems which appeared in the machining process of the aero-engine, and the high-efficiency and energy-saving methods was summarized which would become the technical guidance of high efficiency machining of the aero engine fan blades.
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Yun, Jung Yeul, Shun Myung Shin, Dong Won Lee, Jong Nam Kim, and Jei Pil Wang. "Fabrication of Fe-36Ni Alloy Powder from its Scrap." Advanced Materials Research 747 (August 2013): 619–22. http://dx.doi.org/10.4028/www.scientific.net/amr.747.619.
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Ni-based superalloys are used extensively in the hot section of gas turbine engines owing to their inherent elevated temperature strength and creep resistance. As such, aircraft engine manufactures are continually striving to push the envelope of the capabilities of such high temperature structure materials in order to increase both engine performance and efficiency [1,2].
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Setiyawati, Defi. "Analisis Perbandingan Performa Saat Takeoff Pada Engine CFM56-7b Dengan Konfigurasi Thrust Rating 26300 Lbs Dan 27300 Lbs." Jurnal Teknologi Kedirgantaraan 7, no. 1 (January 31, 2022): 7–14. http://dx.doi.org/10.35894/jtk.v7i1.51.
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The CFM 56-7B engine is manufactured by CFM International which is used on the B737-600/700/800/900 aircraft. This engine has several variations of the thrust rating with varying performance. Engine performance parameters include Thrust, Specific Fuel Consumption (SFC), Core Speed (N2), and Exhaust Gas Temperature (EGT). Performance testing can be done using the Engine Test Cell. However, the engine test cell is a calibrated tool, which allows deviation of the test results. Then the performance calculation is done using the formula in the Engine Shop Manual - Test 003 - Engine Acceptance Test to find out the engine performance during the takeoff phase at the highest thrust rating of 26300 lbs and 27300 lbs and compare the performance of the two engines. Comparison of the calculation results states that an engine with a thrust rating of 26300 lbs is superior to Exhaust Gas Temperature, while an engine with a thrust rating of 27300 lbs has advantages at Thrust, Specific Fuel Consumption and Core Speed (N2).
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Giesecke, Daniel, Marcel Lehmler, Jens Friedrichs, Jason Blinstrub, Lothar Bertsch, and Wolfgang Heinze. "Evaluation of ultra-high bypass ratio engines for an over-wing aircraft configuration." Journal of the Global Power and Propulsion Society 2 (October 17, 2018): 493–515. http://dx.doi.org/10.22261/jgpps.8shp7k.
Full textAbstract:
Today, main hub airports are already at their capacity limit and hence, smaller airports have become more interesting for providing point-to-point connections. Unfortunately, the use of regional airports induces an increased environmental footprint for the population living around it. In an attempt to solve the related problems, the research project Coordinated Research Centre 880 aims to examine the fundamentals of a single-aisle aircraft with active high-lift configuration powered by two geared ultra-high bypass turbofan engines mounted over the wing. Low direct operating costs, noise shielding due to the over-wing configuration, and short runway lengths are the main advantages. Highlighting the performance, economical and noise benefits of a geared ultra-high bypass engine is the key aim of this paper. This assessment includes a correspondingly adjusted aircraft. Open literature values are applied to design the two investigated bypass ratios; a reference engine with a bypass ratio of 5 and 17 respectively. This study shows that a careful selection of engine mass flow, turbine entry temperature and overall pressure ratio determines the desirable bypass ratio. The aircraft direct operating costs drop by 5.7% when comparing the designed conventional with a future ultra-high bypass ratio engine. Furthermore, the sound at source for a selected mission and operating condition can be reduced by 7 dB. A variable bypass nozzle area for the ultra-high bypass ratio engine is analysed in terms of performance and operability. An increase of safety margin is shown for the turbofan engine with a variable bypass nozzle. It is concluded that this unconventional aircraft configuration with ultra-high bypass ratio engines mounted over the wing has the potential to relieve main hub airports and reduce the environmental impact.
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Brear, Michael J., Jack L. Kerrebrock, and Alan H. Epstein. "Propulsion System Requirements for Long Range, Supersonic Aircraft." Journal of Fluids Engineering 128, no. 2 (March 8, 2005): 370–77. http://dx.doi.org/10.1115/1.2169810.
Full textAbstract:
This paper discusses the requirements for the propulsion system of supersonic cruise aircraft that are quiet enough to fly over land and operate from civil airports, have trans-pacific range in the order of 11,112km(6000nmi), and payload in the order of 4545kg(10,000lb.). It is concluded that the resulting requirements for both the fuel consumption and engine thrust/weight ratio for such aircraft will require high compressor exit and turbine inlet temperatures, together with bypass ratios that are significantly higher than typical supersonic-capable engines. Several technologies for improving both the fuel consumption and weight of the propulsion system are suggested. Some of these directly reduce engine weight while others, by improving individual component performance, will enable higher bypass ratios. The latter should therefore also indirectly reduce the bare engine weight. It is emphasized, however, that these specific technologies require considerable further development. While the use of higher bypass ratio is a significant departure from more usual engines designed for supersonic cruise, it is nonetheless considered to be a practical option for an aircraft of this kind.