Academic literature on the topic 'Advanced Operation Airbase'
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Journal articles on the topic "Advanced Operation Airbase"
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Pastukhov, A. G., D. N. Bakharev, S. F. Volvak, and R. V. Chernikov. "Pneumatic System of Variable-Force Corn Threshing." Agricultural Machinery and Technologies 13, no. 4 (October 3, 2019): 42–47. http://dx.doi.org/10.22314/2073-7599-2019-13-4-42-47.
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Differentiation of the force applied to the cobs of seed corn in the process of threshing allows minimizing the amount of macro- and micro-damage to the grain, which maintains the potential yield level of this crop. (Research purpose) To develop an automatic control system for active pneumatic elements of the deck of the threshing-and-separating unit capable of varying the pressing force of the spikes applied to the cobs of seed corn in different parts of the threshing chamber to minimize the crop damage. (Materials and methods) The authors have used the methods of system analysis, designing the operating algorithms of automated mechanical systems, electronics and general electrical engineering. (Results and discussions) The authors offer an advanced design of the threshing-and-separating unit for seed corn. The design features an active pneumatic deck with an automatic control system varying the pressing force of separate deck spikes to the cob grain directly in the course of threshing. For air inflating and lowering, two valves are installed in each of the 16 airbags, 32 control relays being used. The operation process is automatized through the Atmega 2560 controller regulating the amount of pressure in the airbags forcing the spikes against the grain in the process of threshing. The authors propose a schematic diagram describing the operation algorithm of the controller with pressure control units in deck airbags. By programming the controller, an operator can change the amount of pressure in the airbags, thus adjusting the force of direct and precise pressing the deck spikes to the corn cobs, for any airbag and in any part of the deck. (Conclusions) It has been determined that the destructive pressing force of 55 Newtons can be achieved in certain combinations of the membrane thickness, the pressure in the airbags and the pressing depth of the spikes. The proposed design of the threshing device with a system of automated pressure control in the deck airbags allows varying the force of threshing, which minimizes the amount of macro- and micro-damage to the seed corn grain and thus maintains the potential yield level of this crop.
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Leong, M. Y., C. S. Smugeresky, V. G. McDonell, and G. S. Samuelsen. "Rapid Liquid Fuel Mixing for Lean-Burning Combustors: Low-Power Performance." Journal of Engineering for Gas Turbines and Power 123, no. 3 (January 1, 2001): 574–79. http://dx.doi.org/10.1115/1.1362318.
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Designers of advanced gas turbine combustors are considering lean direct injection strategies to achieve low NOx emission levels. In the present study, the performance of a multipoint radial airblast fuel injector Lean Burn injector (LBI) is explored for various conditions that target low-power gas turbine engine operation. Reacting tests were conducted in a model can combustor at 4 and 6.6 atm, and at a dome air preheat temperature of 533 K, using Jet-A as the liquid fuel. Emissions measurements were made at equivalence ratios between 0.37 and 0.65. The pressure drop across the airblast injector holes was maintained at 3 and 7–8 percent. The results indicate that the LBI performance for the conditions considered is not sufficiently predicted by existing emissions correlations. In addition, NOx performance is impacted by atomizing air flows, suggesting that droplet size is critical even at the expense of penetration to the wall opposite the injector. The results provide a baseline from which to optimize the performance of the LBI for low-power operation.
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Tömböl, László, Lajos Lóránt Böcz, and János Juhancsik. "A földi telepítésű légvédelem új vezetési rendszere." Haditechnika 55, no. 3 (2021): 64–69. http://dx.doi.org/10.23713/ht.55.3.11.
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A Zrínyi Honvédelmi és Haderőfejlesztési Program (Zrínyi HHP) keretében a földi telepítésű légvédelem eszközállománya is megújul. A légtérvédelmi képesség első új eleme a német Airbus Defence and Space vállalat által gyártott multifunkciós Föld-Levegő Rakéta Műveleti Központ, a SAMOC (Surface-to-Air Missile Operations Center). A SAMOC vezetési eszközként megvalósítja a hozzárendelt földi telepítésű légvédelem összetevőinek stratégiai szintű koordinációját. A beszerzésre vonatkozó szerződést 2018. december 20án írták alá a Honvédelmi Minisztériumban. Rendszerbe állítása – az új kis-közepes hatótávolságú légvédelmi rakétarendszer (NASAMS – National Advanced Surface to Air Missile System) – beszerzésének időpontjához igazodva, azt megelőzően valósul meg.
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Sarter, Nadine B., and David D. Woods. "Team Play with a Powerful and Independent Agent: Operational Experiences and Automation Surprises on the Airbus A-320." Human Factors: The Journal of the Human Factors and Ergonomics Society 39, no. 4 (December 1997): 553–69. http://dx.doi.org/10.1518/001872097778667997.
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Research and operational experience have shown that one of the major problems with pilot-automation interaction is a lack of mode awareness (i.e., the current and future status and behavior of the automation). As a result, pilots sometimes experience so-called automation surprises when the automation takes an unexpected action or fails to behave as anticipated. Alack of mode awareness and automation surprises can be viewed as symptoms of a mismatch between human and machine properties and capabilities. Changes in automation design can therefore be expected to affect the likelihood and nature of problems encountered by pilots. Previous studies have focused exclusively on early generation "glass cockpit" aircraft that were designed based on a similar automation philosophy. To find out whether similar difficulties with maintaining mode awareness are encountered on more advanced aircraft, a corpus of automation surprises was gathered from pilots of the Airbus A-320, an aircraft characterized by high levels of autonomy, authority, and complexity. To understand the underlying reasons for reported breakdowns in human-automation coordination, we also asked pilots about their monitoring strategies and their experiences with and attitude toward the unique design of flight controls on this aircraft.
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Qiu, Jinlong, Sen Su, Aowen Duan, Chengjian Feng, Jingru Xie, Kui Li, and Zhiyong Yin. "Preliminary injury risk estimation for occupants involved in frontal crashes by combining computer simulations and real crashes." Science Progress 103, no. 2 (April 2020): 003685042090875. http://dx.doi.org/10.1177/0036850420908750.
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The fatality rate can be dramatically reduced with the help of emergency medical services. The purpose of this study was to establish a computational algorithm to predict the injury severity, so as to improve the timeliness, appropriateness, and efficacy of medical care provided. The computer simulations of full-frontal crashes with rigid wall were carried out using LS-DYNA and MADYMO under different collision speeds, airbag deployment time, and seatbelt wearing condition, in which a total of 84 times simulation was conducted. Then an artificial neural network is adopted to construct relevance between head and chest injuries and the injury risk factors; 37 accident cases with Event Data Recorder data and information on occupant injury were collected to validate the model accuracy through receiver operating characteristic analysis. The results showed that delta-v, seatbelt wearing condition, and airbag deployment time were important factors in the occupant’s head and chest injuries. When delta-v increased, the occupant had significantly higher level of severe injury on the head and chest; there is a significant difference of Head Injury Criterion and Combined Thoracic Index whether the occupant wore seatbelt. When the airbag deployment time was less than 20 ms, the severity of head and chest injuries did not significantly vary with the increase of deployment time. However, when the deployment time exceeded 20 ms, the severity of head and chest injuries significantly increased with increase in deployment time. The validation result of the algorithm showed that area under the curve = 0.747, p < 0.05, indicating a medium level of accuracy, nearly to previous model. The computer simulation and artificial neural network have a great potential for developing injury risk estimation algorithms suitable for Advanced Automatic Crash Notification applications, which could assist in medical decision-making and medical care.
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Dumakor-Dupey, Nelson K., Sampurna Arya, and Ankit Jha. "Advances in Blast-Induced Impact Prediction—A Review of Machine Learning Applications." Minerals 11, no. 6 (June 3, 2021): 601. http://dx.doi.org/10.3390/min11060601.
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Rock fragmentation in mining and construction industries is widely achieved using drilling and blasting technique. The technique remains the most effective and efficient means of breaking down rock mass into smaller pieces. However, apart from its intended purpose of rock breakage, throw, and heave, blasting operations generate adverse impacts, such as ground vibration, airblast, flyrock, fumes, and noise, that have significant operational and environmental implications on mining activities. Consequently, blast impact studies are conducted to determine an optimum blast design that can maximize the desirable impacts and minimize the undesirable ones. To achieve this objective, several blast impact estimation empirical models have been developed. However, despite being the industry benchmark, empirical model results are based on a limited number of factors affecting the outcomes of a blast. As a result, modern-day researchers are employing machine learning (ML) techniques for blast impact prediction. The ML approach can incorporate several factors affecting the outcomes of a blast, and therefore, it is preferred over empirical and other statistical methods. This paper reviews the various blast impacts and their prediction models with a focus on empirical and machine learning methods. The details of the prediction methods for various blast impacts—including their applications, advantages, and limitations—are discussed. The literature reveals that the machine learning methods are better predictors compared to the empirical models. However, we observed that presently these ML models are mainly applied in academic research.
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Jupp, J. A., and H. J. Price. "Transport aircraft — a challenge for aluminium alloys for the 21st century." Aeronautical Journal 102, no. 1014 (April 1998): 181–88. http://dx.doi.org/10.1017/s0001924000096287.
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AbstractThe anticipated size of the world airliner market over the period 1997-2016, and the resultant requirements for aluminium plate and extrusions to satisfy potential Airbus wing box production is reviewed.The ‘value’ of technology and the threat posed by polymer composites to the future of aluminium alloys for large transport aircraft wing box structures is discussed and the prospect is raised that there may be limited further development potential for conventional aluminium alloys within the civil transport wing context. This may then force a re-evaluation of the role of aluminium-lithium alloys and other non-conventional metallic materials as alternatives to polymer composites.Opportunities to maximise the cost-effectiveness of advanced aluminium alloys are discussed and the potential benefits of closer co-operation between the aircraft and aluminium industries highlighted within a joint technical and commercial framework.The ‘challenge’ to the aluminium industry is described as a continuing requirement to assist the aircraft manufacturer to offer ‘optimum value’ products to the airlines. Otherwise, alternative technologies such as polymer composites will emerge and the pre-eminent position of aluminium in civil transport aircraft will be eroded.
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Baumann, S., T. Neidhardt, and U. Klingauf. "Evaluation of the aircraft fuel economy using advanced statistics and machine learning." CEAS Aeronautical Journal 12, no. 3 (June 19, 2021): 669–81. http://dx.doi.org/10.1007/s13272-021-00508-8.
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AbstractFuel represents a significant proportion of an airline’s operating costs. Statistical analyses and physical models have been used to monitor and estimate fuel consumption up to now, but these can have considerable inaccuracies. This means that, currently, there are no suitable detection methods for the evaluation of aircraft retrofits, of which some only suggest a fuel efficiency potential in the tenths of a percent range. This article examines suitable assessments of the fuel economy of aircraft and especially aircraft with and without retrofitting. For this purpose, the effects of technical influences such as measurement errors and external uncertainties such as turbulence on the evaluation of the fuel economy are examined in more detail. The focus of the article is on a discussion of possible optimization potentials of conventional statistical evaluation methods, especially regarding possible misinterpretations and spurious correlations. This discussion is exemplarily based on a case study of simulated flight data of an Airbus A320 (with and without improved wing tips (sharklets) as an exemplary retrofit). For this purpose, a suitable simulation environment is presented in which relevant environmental parameters such as wind and turbulence can be set, and measurement errors in the recorded data can be manipulated. It is found that measurement errors as well as turbulence can lead to a bias in key figures that are used for the evaluation of fuel flow signals. The effect of turbulence can partly be mitigated by the use of an improved key figure the authors propose. The investigation is also carried out using a data-based evaluation method to simulate the fuel flow using a machine learning model (random forests), whereby the effects of turbulence and measurement errors significantly influence the fuel flow predicted by the model in the same order of magnitude as potential retrofit measures.
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Hazhiyah, Rika Raudhatul, Lazuardy Rahendra Pinandhita, and Sri Mulyani. "ANALYSIS OF MAINTENANCE PLANNING C01 CHECK IN AIRBUS A320-214 PK-LUM AT BATAM AERO TECHNIC (BAT)." Vortex 3, no. 1 (January 15, 2022): 32. http://dx.doi.org/10.28989/vortex.v3i1.1178.
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Maintenance is all activities undertaken to maintain the aircraft, its aircraft components and equipment in an air condition including inspection, repair, servicing, overhaul and part change. To be able to perform maintenance properly, every aircraft is required to have a maintenance program. . Batam Aero Technic (BAT) handles MRO work on Airbus A320-214 aircraft with registration number PK-LUM. By analyzing the results of the aircraft maintenance planning to find out the comparison of the results of the planning with the implementation of maintenance. This can maximize the implementation of future maintenance so as not to interfere with aircraft flight operations at Batam Aero Technic (BAT). Before carrying out the treatment process, you should do the planning in advance to ensure that the treatment process runs in accordance with the planning made. To find out the treatment process is running in accordance with its planning or not, it will be analyzed using a fiishbone diagram. Fishbone diagrams are generally used in the stage of identifying problems and determining the cause of the problem. This treatment planning analsis process includes analysis of C01 check care implementation, evaluation of the implementation of C01 check treatment program, treatment delay solution, and C01 check care planning. Then from the results of the analysis the author obtained the cause of delays that occur in the field that is difficult to control such as the problem of delays in the availability of materials / spare parts where ordering and delivery time is needed. Therefore the authors propose to multiply the estimated manhours by 2.5 as an alternative to the anticipation of delayed completion of treatment. This is done to minimize the occurrence of delays in manhours on the ground.
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Karpuk, Stanislav, Rolf Radespiel, and Ali Elham. "Assessment of Future Airframe and Propulsion Technologies on Sustainability of Next-Generation Mid-Range Aircraft." Aerospace 9, no. 5 (May 23, 2022): 279. http://dx.doi.org/10.3390/aerospace9050279.
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The present work demonstrates the impact of future airframe and propulsion technologies on the sustainability of potential future medium-range commercial jets with design specifications similar to the Airbus A320-200. Advanced airframe and engine technologies include laminar flow control (LFC), active load alleviation, new materials and structures, and ultra-high bypass ratio turbofan engines. Two aircraft configurations with various design options were compared to determine potentially the best option for the mission profile, which tends to minimize the environmental impact. Each configuration was designed to balance the equivalent CO2 emissions and Direct Operating Costs. Technology sensitivity analyses were performed to investigate the significance of particular technology combinations and determine the ones that improve aircraft sustainability the most. All studies were performed at a conceptual design level using a multi-fidelity design approach to investigate the system-level effects of the technologies. The open-source aircraft design environment SUAVE was extended and integrated with other aircraft design and analysis tools to obtain all required correlations. The aircraft with advanced technologies showed an average reduction in equivalent CO2 emissions of 36% and a 23% reduction in DOC compared to the reference aircraft for a similar mission profile, although aircraft with future technologies may have a 43% higher production cost. The given results indicate that the application of technologies may be commercially successful if technologies achieve expected performance values, despite high development costs. Finally, the technology sensitivity analysis demonstrated the most significant influence of engine-related technologies and laminar flow control compared to other technologies considered in this research. Depending on design and integration complexities, engine technologies can be more achievable in the near future and can substantially reduce the overall emission level.
Dissertations / Theses on the topic "Advanced Operation Airbase"
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(13157530), Vanessa Seekee. "Horn Island, Torres Strait and the 1939-1945 Star Medal." Thesis, 2003. https://figshare.com/articles/thesis/Horn_Island_Torres_Strait_and_the_1939-1945_Star_Medal/20380137.
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This dissertation explores the anomaly of Horn Island, Torres Strait, being classified a non -operational area during World War Two. It explains why this designation was wrong, and why it needed to be changed in order that the men and women who served there be accorded the recognition that they had been striving for since the war concluded. The concrete measure of that recognition comes in the form of the 1939- 1945 Star Medal. This prestigious award is for duty in an area that came under enemy attack during the Second World War, until 1993 restricted to those who served overseas. The dissertation plots the activities of Air Force and Army squadrons and units at Horn Island, both Australian and American, draws on an extensive bank of oral evidence, and focuses on the experiences of those who served there. Their histories portray what life was like at that Advanced Operational Airbase, and demonstrate the effect Horn Island service had on veterans. These are tangible demonstrations and are attested to by the fact that 60 years later the men and women have begun to return. They are being drawn back to their island of service, to walk in the steps of their youth, recapturing a past that will soon be lost to memory. Many bring their descendants to pass down their family's wartime heritage. On 26 October 2001 the 1939-1945 Star Medal finally was awarded to qualifying Tones Strait veterans, a decision that affected thousands of men, and a handful of women, who now hold the physical symbol that their wartime service has been acknowledged. However, for many other Horn Island veterans there is still unfinished business.
Book chapters on the topic "Advanced Operation Airbase"
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Lakkis, Jonathan, and Cees Bil. "Conceptual Design Study of a High-Altitude Mountain Rescue Rotorcraft." In Advances in Transdisciplinary Engineering. IOS Press, 2021. http://dx.doi.org/10.3233/atde210129.
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While there is a market for trekkers venturing into isolated environments, there will also be a market for specialized vehicles to rescue trekkers waylaid by unfortunate circumstance. This paper presents a conceptual design study of a helicopter specifically for rescue operations in extremely high altitude and mountainous terrain. Mt. Everest suffers from overcrowding and a high fluctuation of inexperienced climbers who pose a risk to themselves and other climbers around them. Rescue by fellow climbers when incapacitated is risky and difficult. There is a need for a rescue helicopter capable of hovering and extracting climbers as high up as the summit. However, there are many challenges from multiple disciplines that limit potential solutions. Helicopter sizing, economics, medical treatment, and socio-legislative policies all impact the major decision- making processes. This paper proposes a design that best addresses these issues using currently available technology. Turboshaft engines, contrary to electric motors, loose power with increasing altitude which means that for high-altitude operations it must be overpowered. The novelty of this design concept is the application of a compact coaxial helicopter with a hybrid-electric turboshaft propulsion system which balances the power required in high-altitude hover and cruise. The feasibility of this design is then compared to a traditional helicopter using a theoretically sized turboshaft engine. Many components from the Airbus H135 are integrated to reduce cost.
Conference papers on the topic "Advanced Operation Airbase"
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Kraft, Joern, and Stefan Kuntzagk. "Engine Fleet-Management: The Use of Digital Twins From a MRO Perspective." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63336.
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Engine operating cost is a major contributor to the direct operating cost of aircraft. Therefore, the minimization of engine operating cost per flight-hour is a key aspect for airlines to operate successfully under challenging market conditions. The interaction between maintenance cost, operating cost, asset value, lease and replacement cost describes the area of conflict in which engine fleets can be optimized. State-of-the-art fleet management is based on advanced diagnostic and prognostic methods on engine and component level to provide optimized long-term removal and work-scoping forecasts on fleet level based on the individual operation. The key element of these methods is a digital twin of the active engines consisting of multilevel models of the engine and its components. This digital twin can be used to support deterioration and failure analysis, predict life consumption of critical parts and relate the specific operation of a customer to the real and expected condition of the engines on-wing and at induction to the shop. The fleet management data is constantly updated based on operational data sent from the engines as well as line maintenance and shop data. The approach is illustrated along the real application on the CFM56-5C, a mature commercial two-spool high bypass engine installed on the Airbus A340-300. It can be shown, that the new methodology results in major improvements on the considered fleets.
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Andreini, Antonio, Cosimo Bianchini, Gianluca Caciolli, Bruno Facchini, Andrea Giusti, and Fabio Turrini. "Multi-Coupled Numerical Analysis of Advanced Lean Burn Injection Systems." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26808.
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Lean burn aero-engine combustors usually exploit advanced prefilming airblast injection systems in order to promote the formation of highly homogeneous air-fuel mixtures with the main aim of reducing NOx emissions. The combustion process is strongly influenced by the liquid fuel preparation and a reliable prediction of pollutant emissions requires proper tools able to consider the most important aspects characterizing liquid film evolution and primary breakup. This paper presents the numerical analysis of an advanced lean burn injection system using a multi-coupled two-phase flow three-dimensional solver developed on the basis of OpenFOAM modelling and numerics. The solver allows the coupled solution of gas-phase, droplets and liquid film exploiting correlation-based and theoretical models for liquid film primary atomization. A detailed analysis of the liquid film evolution is presented together with an investigation of the influence of film modelling and primary breakup on the combustion process at different operating conditions. The combustion field is strongly influenced by the characteristics of droplet population generated by the liquid film and this study proposes a computational setup, suitable for industrial calculations, able to account for all the main physical processes that characterize advanced prefilming airblast injection systems.
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Leong, May Y., Craig S. Smugeresky, Vincent G. McDonell, and G. Scott Samuelsen. "Rapid Liquid Fuel Mixing for Lean-Burning Combustors: Low-Power Performance." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0116.
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Designers of advanced gas turbine combustors are considering lean direct injection strategies to achieve low NOx emission levels. In the present study, the performance of a multipoint radial airblast fuel injector (“Lean Burn Injector—LBI”) is explored for various conditions that target low-power gas turbine engine operation. Reacting tests were conducted in a model can combustor at 4 atm and 6.6 atm, and at a dome air preheat temperature of 533 K, using Jet-A as the liquid fuel. Emissions measurements were made at equivalence ratios between 0.37 and 0.65. The pressure drop across the airblast injector holes was maintained at 3% and 7–8%. The results indicate that the LBI performance for the conditions considered is not sufficiently predicted by existing emissions correlations. In addition, NOx performance is impacted by atomizing air flows, suggesting that droplet size is critical even at the expense of penetration to the wall opposite the injector. The results provide a baseline from which to optimize the performance of the LBI for low-power operation.
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Heindel, Theodore J., Timothy B. Morgan, Thomas J. Burtnett, Julie K. Bothell, Danyu Li, Alberto Aliseda, and Nathanael Machicoane. "High-Speed Flow Visualization of a Canonical Airblast Atomizer Using Synchrotron X-Rays." In ASME-JSME-KSME 2019 8th Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/ajkfluids2019-4992.
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Abstract Liquid sprays play a key role in many engineering processes and the dynamics at the nozzle exit have a significant impact on the downstream spray characteristics. However, visualizing the spray in this region is extremely challenging because, under most operating conditions, the spray is optically dense. High intensity white beam X-rays, like those found at the Advanced Photon Source (APS) at Argonne National Laboratory, can be used to produce time-resolved measurements of the liquid-gas structures in the spray near-field region. In this study, high temporal and spatial resolution X-ray images were acquired at the 7-BM beamline at APS of an atomization process using a canonical airblast atomizer consisting of coaxial liquid and gas jets. Unique flow structures were observed under various operating conditions, including bag, ligament, wisp, droplet, and air bubble formation, as well as hollowing of the liquid core into a crown at the liquid needle exit. Conditions where these structures exist are presented and their impact on spray formation are discussed.
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Micklow, Gerald J., and Michael Benjamin. "Three Dimensional Analysis of Advanced Swirl Vane/Nozzle Assemblies." In ASME 1996 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1996. http://dx.doi.org/10.1115/96-gt-226.
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The performance of high shear axial inflow/radial outflow airblast fuel injectors for advanced gas turbine combustors is highly dependent on the design of the swirl vanes. Curved vanes usually exhibit lower losses but straight vanes are also used due to lower cost and ease of manufacture. These type of vanes often operate under highly stalled conditions with high total pressure loss and a highly non-uniform exit velocity profile. This may produce poor fuel atomization with a non-uniform combustor fuel distribution resulting in lowered combustor efficiency and increased pollutant emissions. Properly designed vanes result in a greatly reduced total pressure loss. The exit velocity distribution is more uniform and higher in magnitude which can result in improved fuel atomization and distribution in the combustor. The present study investigates two curved swirler/nozzle shroud configurations operating at 1 and 10 atmospheres pressure for the same inlet temperature of 293°K. The first configuration was a twisted curved vane with thickness where the turning angle varied non-linearly from hub to tip with a maximum turning at the tip of 70 degrees. The second configuration was a curved vane with a linear variation of turning with 70 degrees turning at the tip. The results from a three dimensional viscous numerical flow simulation of these configurations shows similar performance for all cases investigated. The non-linear twisted vane however, had an approximately 3% higher mass flow rate than the vane with the linear variation in turning for the same exit static pressure at the hub. One problem which existed for all the conditions analyzed was a high loss region near the vane tip. This was due to the interaction with the shroud. As the flow exits the vane row and progresses along the nozzle outer lip, the flow area increases. This condition along with the streamline curvature effect of the outer nozzle lip causes an adverse pressure gradient to be formed in this region. This adverse pressure gradient causes the flow to separate from the vane suction surface. The problem initiated in the region of 70% span and increased in magnitude to the vane tip.
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Lai, Mark K. "CFD Analysis of Liquid Spray Combustion in a Gas Turbine Combustor." In ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/97-gt-309.
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A numerical method is presented for predicting steady, three-dimensional, turbulent, liquid spray combusting flows in a gas turbine combustor. The Eulerian conservation equations for gas flow and the Lagrangian conservation equations for discrete fuel liquid droplets were solved. The trajectory computation of the fuel droplets provided the source terms for all the gas-phase equations. A standard k-ε submodel was used for turbulence. The combustion submodel used was a global local equilibrium model, where chemical species (CxHy, O2, CO2, H2O, CO, H2 and N2) approached local thermodynamic equilibrium with a rate determined by a combination of local turbulent mixing and global chemical kinetics times. The numerical methodology for gas-phase calculations involved a staggered finite-volume formulation with a multi-block curvilinear orthogonal coordinate computational grid, and the PISO algorithm. This numerical code was applied to a model gas turbine combustor similar to that of the Allison 570KF currently in use by the Canadian Navy. The combustor was equipped with an advanced airblast fuel nozzle. The calculations included the analysis of the internal passages of the fuel nozzle. Through the numerical study at full-power and low-cruise operating conditions, a better understanding of the physical processes of flow and temperature fields inside the primary zone was obtained. Predicted hot spots corresponded to locations where deterioration of the combustor liner has been observed in practice.
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Silva, Manuel, Nicolas Tantot, Serge Selezneff, Mike Walsh, Rose Nyatando, Erik Johann, Thomas Klauke, Michele Coppola, and André Kando. "Advanced Aero-Engines Technology Enablers: An Overview of the European Project E-BREAK." In ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2016. http://dx.doi.org/10.1115/gt2016-56572.
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This paper describes research carried out in the European Commission co-funded project E-BREAK (Engine BREAK through components and subsystems) focused on development of generic enabling technologies for new aero-engines. A global market forecast (2015–2034) from Airbus [1], depicts an average growth rate of 4.6% per year. Air traffic is forecasted to double in the next 15 years. It is expected, to triple in the next 20 years, according to the speech given by RRUK CEO during the Aerodays 2015 in London [2]. This high level of growth in demand for air travel represents huge opportunities as well as significant challenges for the aerospace industry. Research and Technology through collaborative European projects addresses the environmental penalties of air traffic. Europe’s aviation industry therefore faces a huge challenge to satisfy the demand whilst guaranteeing competitiveness, safety and more environmentally friendly air travel. Innovative engine configurations consequently need to be investigated in order to reduce significantly the pollutant emissions (15 to 20% for fuel consumption and CO2 and 80% reduction for NOx). Such reductions can only be achieved by considering innovative components that could be integrated and optimized in new engine configurations. In response to the above demands, aero-engine manufacturers are constantly aiming to improve gas turbine efficiency for two main reasons: to reduce environmental impact and to minimize operating costs. The E-BREAK project is aimed at the development of generic enabling technologies needed to address the challenges for future engines with higher overall pressure ratios (OPR) and bypass ratio (BPR). These technologies are developed at subsystem and component level and validated in test rigs which are equivalent to Technical Readiness Level (TRL) 5. The utility of the developed technologies are assessed using four standard study powerplants. These are turboshaft, regional turbofan, mid-size open rotor, and large turbofan, covering most of the expected future commercial aero-engine market. This article describes the technical approach followed in E-BREAK for the various technologies being investigated, these are: • Advanced sealing to reduce oil and air leakages • Variability control to ensure stability of thermodynamic cycle • High temperature resistant material and abradables to prevent fast degradation at high temperatures • Light material to prevent significant mass increase • Health monitoring system to anticipate sub-systems degradation The envisaged outcomes from E-BREAK are enablers to other EU-funded research projects focused on module maturation progress, such as LEMCOTEC dealing with high OPR modules and ENOVAL dealing with high BPR LP components.