Relevant bibliographies by topics / Gas Turbine Engine Control

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Gas Turbine Engine Control'

Author: Grafiati
Published: 6 September 2023

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Journal articles on the topic "Gas Turbine Engine Control"

1

Niculescu, Filip, Claudia Borzea, Adrian Savescu, Andrei Mitru, and Mirela Letitia Vasile. "Automation and Electronic Control of Marine Gas Turbine Engine for Ship Revamp." Technium: Romanian Journal of Applied Sciences and Technology 2, no. 4 (June 10, 2020): 98–108. http://dx.doi.org/10.47577/technium.v2i4.923.

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Gas turbines used in propulsion ensure increased efficiency and safety, with a very good power / weight ratio and with low maintenance and operation costs. Due to becoming out-of-date and reaching the maximum operation hours and expected lifetime, which can cause malfunctioning, older turbine engines on frigates need to be replaced with newer generation propulsion engines. The paper presents the replacement of the turbine engine on a defence frigate, focusing on the automation and electronic control solution employed for a propulsion turbine, integrating state-of-the-art techniques. The electronic system ensures control, monitoring and alarm functions, including overspeed protection. A local control panel interfacing the PLC displays the operating parameters and engine controls, also providing maintenance and calibration sequences. The proposed solution enables both the local and the remote control of the ship’s gas turbine.
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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.
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Kerr, L. J., T. S. Nemec, and G. W. Gallops. "Real-Time Estimation of Gas Turbine Engine Damage Using a Control-Based Kalman Filter Algorithm." Journal of Engineering for Gas Turbines and Power 114, no. 2 (April 1, 1992): 187–95. http://dx.doi.org/10.1115/1.2906571.

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A second-generation Kalman filter algorithm is described that has sufficient accuracy and response for real-time detection and estimation of gas turbine engine gas path damage caused by normal wear, mechanical failures, and ingestion of foreign objects. The algorithm was developed for in-flight operation of aircraft engines but also has application for marine and industrial gas turbines. The control measurement and microcomputer requirements are described. The performance and sensitivity to engine transients and measurement errors is evaluated. The algorithm is demonstrated with actual engine data of ice and bird ingestion tests.
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Sylvestre, R. A., and R. J. Dupuis. "The Evolution of Marine Gas Turbine Controls." Journal of Engineering for Gas Turbines and Power 112, no. 2 (April 1, 1990): 176–81. http://dx.doi.org/10.1115/1.2906158.

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The background and evolution of gas turbine fuel controls is examined in this paper from a Naval perspective. The initial application of aeroderivative gas turbines to Navy ships utilized the engine’s existing aircraft fuel controls, which were coupled to the ship’s hydropneumatic machinery control system. These engines were adapted to Naval requirements by including engine specific functions. The evolution of Naval gas turbine controllers first to analog electronic, and more recently, to distributed digital controls, has increased the system complexity and added a number of levels of machinery protection. The design of a specific electronic control module is used to illustrate the current state of the technology. The paper concludes with a discussion of the further need to address the issues of fuel handling, metering and control in Navy ships with particular emphasis on integration in the marine environment.
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Tovkach, Serhii. "Control Laws of the Aviation Gas Turbine Engine." Electronics and Control Systems 2, no. 72 (September 23, 2022): 20–25. http://dx.doi.org/10.18372/1990-5548.72.16938.

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The article is devoted to the solution of an important scientific and applied problem of improving the dynamic characteristics of an aviation engine and ensuring flight safety and the efficiency of aircraft operation, taking into account the properties of adaptive control of an aviation gas turbine engine: <structure><functioning><adaptation><development>. Based on the concept of creating perspective aviation engines with an increased level of control automation and with units operating at elevated temperatures and protected from high-energy electromagnetic radiation, the basic laws of controlling an aviation gas turbine engine in throttle modes, low-throttle mode, gas intake and discharge modes, and start-up mode are defined. To improve the working process of the engine, it is proposed to use the gas turbine engine control system as a mechatronic system based on the principle of adaptation. With the help of the Laplace transformation, the dynamic characteristics of the power plant were determined and the mathematical model of the power plant was investigated as a constructive aspect of the automatic control system. The gas turbine and the supersonic air manifold can to some extent be considered as independent control objects, replacing the connections between them with disturbing influences. For the control and limitation circuits, it is necessary to create control programs that calculate the values of the control parameters of the turbocharger rotor speed and gas temperature behind the turbine. Regulation of fuel consumption is carried out according to the derivative of the control parameters.
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Wright, W. E., and J. C. Hall. "Advanced Aircraft Gas Turbine Engine Controls." Journal of Engineering for Gas Turbines and Power 112, no. 4 (October 1, 1990): 561–64. http://dx.doi.org/10.1115/1.2906205.

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With the advent of vectored thrust, vertical lift, and fly-by-wire aircraft, the complexity of aircraft gas turbine control systems has evolved to the point wherein they must approach or equal the reliability of current quad redundant flight control systems. To advance the technology of high-reliability engine controls, one solution to the Byzantine General’s problem (Lamport et al., 1982) is presented as the foundation for fault tolerant engine control architecture. In addition to creating a control architecture, an approach to managing the architecture’s redundancy is addressed.
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Кулик, Микола Сергійович, Володимир Вікторович Козлов, and Лариса Георгіївна Волянська. "AUTOMATION CONTROL SYSTEM OF TECHNICAL CONDITION OF GAS TURBINE ENGINE COMPRESSOR." Aerospace technic and technology, no. 8 (August 31, 2019): 121–28. http://dx.doi.org/10.32620/aktt.2019.8.18.

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The article is devoted to one of the approaches to the construction of an automated system for solving the problems of diagnostics and monitoring of the flow duct of aircraft gas turbine engines and gas turbine plants. Timely detection of faults and subsequent monitoring of their development in operation are possible thanks to automated systems for assessing the technical condition of engines. This is particularly relevant in operating conditions as the knowledge of the technical condition of the engine is necessary in any engine maintenance system allows to choose the content and timing of maintenance, repair of the flow duct of gas turbine engines and gas turbine plants, as well as commissioning. The engineering technique, which can be applied at performance of maintenance and at stages of tests and debugging of aircraft engines, is considered. The automated system implements a method of measuring the air flow through the compressor and a technique for assessing the technical condition of the compressor by the relative change in air flow. To determine the air flow rate through the gas turbine engine, it is sufficient to measure only static pressure values in the flow part. The static pressure receivers are not located in the flow part and do not obscure it, and thus do not affect the compressor gas dynamic stability margin. The inspection area is selected for measuring in the flow duct of the air intake. Static pressure in the maximum and minimum cross sections of the chosen area is measured; the maximum cross-section area of the flow duct, the total temperature of the air flow is measured outside the air intake. To determine the air flow rate, the functional dependence of the air flow rate on the static pressure is used. The algorithm for monitoring and diagnosing the operating condition of the engine is based on a comparison of the actual values of air flow rate with the air flow rate determined during the control tests or when using a mathematical model adapted for this gas turbine engine. The positive effect of the using of the proposed automated control system of technical condition is that the air flow rate measured under operating conditions will significantly increase the objectivity of the control of the operation and technical condition of the gas turbine engine.
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Al-Hamdan, Qusai Z., and Munzer S. Y. Ebaid. "Modeling and Simulation of a Gas Turbine Engine for Power Generation." Journal of Engineering for Gas Turbines and Power 128, no. 2 (April 27, 2005): 302–11. http://dx.doi.org/10.1115/1.2061287.

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The gas turbine engine is a complex assembly of a variety of components that are designed on the basis of aerothermodynamic laws. The design and operation theories of these individual components are complicated. The complexity of aerothermodynamic analysis makes it impossible to mathematically solve the optimization equations involved in various gas turbine cycles. When gas turbine engines were designed during the last century, the need to evaluate the engines performance at both design point and off design conditions became apparent. Manufacturers and designers of gas turbine engines became aware that some tools were needed to predict the performance of gas turbine engines especially at off design conditions where its performance was significantly affected by the load and the operating conditions. Also it was expected that these tools would help in predicting the performance of individual components, such as compressors, turbines, combustion chambers, etc. At the early stage of gas turbine developments, experimental tests of prototypes of either the whole engine or its main components were the only method available to determine the performance of either the engine or of the components. However, this procedure was not only costly, but also time consuming. Therefore, mathematical modelling using computational techniques were considered to be the most economical solution. The first part of this paper presents a discussion about the gas turbine modeling approach. The second part includes the gas turbine component matching between the compressor and the turbine which can be met by superimposing the turbine performance characteristics on the compressor performance characteristics with suitable transformation of the coordinates. The last part includes the gas turbine computer simulation program and its philosophy. The computer program presented in the current work basically satisfies the matching conditions analytically between the various gas turbine components to produce the equilibrium running line. The computer program used to determine the following: the operating range (envelope) and running line of the matched components, the proximity of the operating points to the compressor surge line, and the proximity of the operating points at the allowable maximum turbine inlet temperature. Most importantly, it can be concluded from the output whether the gas turbine engine is operating in a region of adequate compressor and turbine efficiency. Matching technique proposed in the current work used to develop a computer simulation program, which can be served as a valuable tool for investigating the performance of the gas turbine at off-design conditions. Also, this investigation can help in designing an efficient control system for the gas turbine engine of a particular application including being a part of power generation plant.
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Zhang, Tian Gang, and Xiao Yun Hou. "NOx Emission Control in Gas Turbines." Applied Mechanics and Materials 66-68 (July 2011): 319–21. http://dx.doi.org/10.4028/www.scientific.net/amm.66-68.319.

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The increase, in recent years, in the size and efficiency of gas turbines burning natural gas in combined cycle has occurred against a background of tightening environmental legislation on the emission of nitrogen oxides. The higher turbine entry temperatures required for efficiency improvement tend to increase NOX production. To reduce NOX emissions, new engine core configurations with heat management and active systems, as well as advanced combustor technology, have to be investigated. This paper reviews the various approaches adopted by the main gas turbine manufacturers which are achieving low levels of NOX emission from natural gas combustion.
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Kazhaev, V. P., D. Y. Kiselev, and Y. V. Kiselev. "DIAGNOSTIC MODEL OF HELICOPTER TURBOSHAFT ENGINE." Izvestiya of Samara Scientific Center of the Russian Academy of Sciences 25, no. 1 (2023): 99–106. http://dx.doi.org/10.37313/1990-5378-2023-25-1-99-106.

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The article presents a qualitative assessment of the impact on the engine components characteristics of the malfunction occurrence in the flow part of the aviation gas turbine engines, which lead to changes in its geometry. Using the example of a compressor, it is shown that when defects appear in it, two of its characteristics are deformed: efficiency and pressure characteristics (which is confirmed by a significant number of studies). It is concluded that in order to reliably diagnose aviation gas turbine engines by thermogasodynamic parameters, the mathematical model must take into account the change in two characteristics for each engine component of the flow part (and not only the change in the characteristics of the efficiency of the nodes). A linear mathematical model of a helicopter turboshaft turbine engine is presented and the results of calculating the influence coefficient for a given control law are presented. The peculiarity of the presented model is that the state of each engine component is characterized by two state parameters: for compressors, this is the head characteristic and the efficiency characteristic, for turbines, performance characteristics and efficiency.
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Dissertations / Theses on the topic "Gas Turbine Engine Control"

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Thompson, Haydn Ashley. "Parallel processing applications for gas turbine engine control." Thesis, Bangor University, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.254683.

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Churchhouse, Stephen Paul. "Multivariable control of a propfan engine." Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303222.

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Keng, W. "Gas turbine engine control and performance enhancement with fuzzy logic." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/11028.

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Gas turbine engine performance improvement has been requested continuously for both military and commercial applications due t various reasons. One of the issues is to save fuel and/or to increase the engine life to meet the multi-mission and operation cost economics requirements. I order to satisfy the customers' requirements, the engine manufacturers invested a lot of money and time if the gas turbine performance improvement. The most straight forward and simple approach is to trade the excess remained surge margins for performance. NASA has demonstrated the feasibility of this concept in their F-15 Highly Integrated Digital Electronic Control and Performance Seeking Control programs. It offers not only obvious benefits if the overall system performance improvement but also cost effective operations such a fuel saving and extended component life. Those were carried out with traditional control approaches which have to face the modelling difficulties. ' Due to successful control implementations of fuzzy logic if various environment of uncertainties, a proportional plus integral z logic controller if proposed. The fuzzy logic control system simulation results prove that the fuzzy logic controller is appropriate for gas turbine engine control. Basic fuzzy logic control concept is used with new approaches to simplifying the fuzzy logic controller. I order to enhance the engine performance, fuzzy logic control concept is used to optimize the engine performance parameters. A time function linear control scheme is proposed to the engine to a new operation location System simulation results prove the new methodology. It has to be understood that the engine model used if this research is not representative of a gas turbine, but it `is appropriate for the fuzzy logic control design analysis and simulation.
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Mahmoud, Saad M. "Effective optimal control of a fighter aircraft engine." Thesis, Loughborough University, 1988. https://dspace.lboro.ac.uk/2134/7287.

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Typical modem fighter aircraft use two-spool, low by-pass ratio, turbojet engines to provide the thrust needed to carry out the combat manoeuvres required by present-day air warfare tactics. The dynamic characteristics of such aircraft engines are complex and non-linear. The need for fast, accurate control of the engine throughout the flight envelope is of paramount importance and this research was concerned with the study of such problems and subsequent design of an optimal linear control which would improve the engine's dynamic response and provide the required correspondence between the output from the engine and the values commanded by a pilot. A detailed mathematical model was derived which, in accuracy and complexity of representation, was a large improvement upon existing analytical models, which assume linear operation over a very small region of the state space, and which was simpler than the large non-analytic representations, which are based on matching operational data. The non-linear model used in this work was based upon information obtained from DYNGEN, a computer program which is used to calculate the steady-state and transient responses of turbojet and turbofan engines. It is a model of fifth order which, it is shown, correctly models the qualitative behaviour of a representative jet engine. A number of operating points were selected to define the boundaries used for the flight envelope. For each point a performance investigation was carried out and a related linear model was established. By posing the problem of engine control as a linear quadratic problem, in which the constraint was the state equation of the linear model, control laws appropriate for each operating point were obtained. A single control was effective with the linear model at every point. The same control laws were then applied to the non-linear mathematical model adjusted for each operating point, and the resulting responses were carefully studied to determine if one single control law could be used with all operating points. Such a law was established. This led, naturally, to the determination of an optimal linear tracking control law, and a further investigation to determine whether there existed an optimal non-linear control law for the non-linear model. In the work presented in this dissertation these points are fully discussed and the reasons for choosing to find an optimal linear control law for the non-linear model by solving the related two-point, boundary value problem using the method of quasilinearisation are presented. A comparison of the effectiveness of the respective optimal control laws, based upon digital simulation, is made before suggestions and recommendations for further work are presented.
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Gomma, Hesham Wagih. "Robust and predictive control of 1.5 MW gas turbine engine." Thesis, University of Exeter, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.302533.

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Keng, W. "Gas turbine engine control and performance enchancement with fuzzy logic." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/11028.

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Gas turbine engine performance improvement has been requested continuously for both military and commercial applications due t various reasons. One of the issues is to save fuel and/or to increase the engine life to meet the multi-mission and operation cost economics requirements. I order to satisfy the customers' requirements, the engine manufacturers invested a lot of money and time if the gas turbine performance improvement. The most straight forward and simple approach is to trade the excess remained surge margins for performance. NASA has demonstrated the feasibility of this concept in their F-15 Highly Integrated Digital Electronic Control and Performance Seeking Control programs. It offers not only obvious benefits if the overall system performance improvement but also cost effective operations such a fuel saving and extended component life. Those were carried out with traditional control approaches which have to face the modelling difficulties. ' Due to successful control implementations of fuzzy logic if various environment of uncertainties, a proportional plus integral z logic controller if proposed. The fuzzy logic control system simulation results prove that the fuzzy logic controller is appropriate for gas turbine engine control. Basic fuzzy logic control concept is used with new approaches to simplifying the fuzzy logic controller. I order to enhance the engine performance, fuzzy logic control concept is used to optimize the engine performance parameters. A time function linear control scheme is proposed to the engine to a new operation location System simulation results prove the new methodology. It has to be understood that the engine model used if this research is not representative of a gas turbine, but it `is appropriate for the fuzzy logic control design analysis and simulation.
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Chung, Gi Yun. "An analytical approach to real-time linearization of a gas turbine engine model." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/50702.

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A recent development in the design of control system for a jet engine is to use a suitable, fast and accurate model running on board. Development of linear models is particularly important as most engine control designs are based on linear control theory. Engine control performance can be significantly improved by increasing the accuracy of the developed model. Current state-of-the-art is to use piecewise linear models at selected equilibrium conditions for the development of set point controllers, followed by scheduling of resulting controller gains as a function of one or more of the system states. However, arriving at an effective gain scheduler that can accommodate fast transients covering a wide range of operating points can become quite complex and involved, thus resulting in a sacrifice on controller performance for its simplicity. This thesis presents a methodology for developing a control oriented analytical linear model of a jet engine at both equilibrium and off-equilibrium conditions. This scheme requires a nonlinear engine model to run onboard in real time. The off-equilibrium analytical linear model provides improved accuracy and flexibility over the commonly used piecewise linear models developed using numerical perturbations. Linear coefficients are obtained by evaluating, at current conditions, analytical expressions which result from differentiation of simplified nonlinear expressions. Residualization of the fast dynamics states are utilized since the fast dynamics are typically outside of the primary control bandwidth. Analytical expressions based on the physics of the aerothermodynamic processes of a gas turbine engine facilitate a systematic approach to the analysis and synthesis of model based controllers. In addition, the use of analytical expressions reduces the computational effort, enabling linearization in real time at both equilibrium and off-equilibrium conditions for a more accurate capture of system dynamics during aggressive transient maneuvers. The methodology is formulated and applied to a separate flow twin-spool turbofan engine model in the Numerical Propulsion System Simulation (NPSS) platform. The fidelity of linear model is examined by validating against a detailed nonlinear engine model using time domain response, the normalized additive uncertainty and the nu-gap metric. The effects of each simplifying assumptions, which are crucial to the linear model development, on the fidelity of the linear model are analyzed in detail. A case study is performed to investigate the case when the current state (including both slow and fast states) of the system is not readily available from the nonlinear simulation model. Also, a simple model based control is used to illustrate benefits of using the proposed modeling approach.
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Stambaugh, Craig T. (Craig Todd) 1960. "Improving gas turbine engine control system component optimization by delaying decisions." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/91787.

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Bae, Jinwoo W. "An experimental study of surge control in a helicopter gas turbine engine." Thesis, Massachusetts Institute of Technology, 1998. http://hdl.handle.net/1721.1/50319.

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Villarreal, Daniel Christopher. "Digital Fuel Control for a Lean Premixed Hydrogen-Fueled Gas Turbine Engine." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34974.

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Hydrogen-powered engines have been gaining increasing interest due to the global concerns of the effects of hydrocarbon combustion on climate change. Gas turbines are suitable for operation on hydrogen fuel. This thesis reports the results of investigations of the special requirements of the fuel controller for a hydrogen gas turbine. In this investigation, a digital fuel controller for a hydrogen-fueled modified Pratt and Whitney PT6A-20 turboprop engine was successfully designed and implemented. Included in the design are safety measures to protect the operating personnel and the engine. A redundant fuel control is part of the final design to provide a second method of managing the engine should there be a malfunction in any part of the primary controller.

Parallel to this study, an investigation of the existing hydrogen combustor design was performed to analyze the upper stability limits that were restricting the operability of the engine. The upstream propagation of the flame into the premixer, more commonly known as a flashback, routinely occurred at 150 shaft horsepower during engine testing. The procedures for protecting the engine from a flashback were automated within the fuel controller, significantly reducing the response time from the previous (manual) method. Additionally, protection measures were added to ensure the inter-turbine temperature of the engine did not exceed published limits. Automatic engine starting and shutdown procedures were also added to the control logic, minimizing the effort needed by the operator. The tested performance of the engine with each of the control functions demonstrated the capability of the controller.

Methods to generate an engine-specific fuel control map were also studied. The control map would not only takes into account the operability limits of the engine, but also the stability limits of the premixing devices. Such a map is integral in the complete design of the engine fuel controller.
Master of Science

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Books on the topic "Gas Turbine Engine Control"

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D, Southwick Robert, Gallops George W, and United States. National Aeronautics and Space Administration., eds. High stability engine control (HISTEC). [Washington, DC]: National Aeronautics and Space Administration, 1996.

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C, DeLaat John, and NASA Glenn Research Center, eds. Active combustion control for aircraft gas turbine engines. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2000.

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Lattime, Scott B. Turbine engine clearance control systems: Current practices and future directions. Cleveland, Ohio: National Aeronautics and Space Administration, Glenn Research Center, 2002.

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Haas, David William. The instrumentation design and control of a T63-A-700 gas turbine engine. Monterey, Calif: Naval Postgraduate School, 1996.

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D, Metz Stephen. Survey of gas tubine control for application to marine gas turbine propulsion system control. Monterey, Calif: Naval Postgraduate School, 1989.

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Stammettii, Vincent A. Survey and analysis of marine gas turbine control after 1975. Monterey, Calif: Naval Postgraduate School, 1988.

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Center, Lewis Research, ed. Ceramic thermal barrier coatings for electric utility gas turbine engines. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1986.

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Center, Lewis Research, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, eds. Turbine engine hot section technology 1986: Proceedings of a conference. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Miller, Robert A. Thermal barrier coatings for gas turbine and diesel engines. [Washington, D.C.]: NASA, 1990.

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J, Brindley W., Bailey M. Murray, and United States. National Aeronautics and Space Administration., eds. Thermal barrier coatings for gas turbine and diesel engines. [Washington, D.C.]: NASA, 1990.

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Book chapters on the topic "Gas Turbine Engine Control"

1

Kulikov, Gennady G., and Haydn A. Thompson. "Stochastic Gas Turbine Engine Models." In Advances in Industrial Control, 217–32. London: Springer London, 2004. http://dx.doi.org/10.1007/978-1-4471-3796-2_12.

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Kulikov, Gennady G., and Haydn A. Thompson. "Introduction to Gas Turbine Engine Control." In Advances in Industrial Control, 1–13. London: Springer London, 2004. http://dx.doi.org/10.1007/978-1-4471-3796-2_1.

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Thompson, Haydn A. "Failure Management and its Application in Gas Turbine Engine Control." In Parallel Processing for Jet Engine Control, 126–82. London: Springer London, 1992. http://dx.doi.org/10.1007/978-1-4471-1972-2_6.

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Singh, Richa, P. S. V. Nataraj, and Arnab Maity. "Nonlinear Control of a Gas Turbine Engine with Reinforcement Learning." In Lecture Notes in Networks and Systems, 105–20. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-89880-9_8.

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Solomon, Ady. "Dynamic Modeling of Airborne Gas Turbine Engines." In Topics in Control and its Applications, 189–205. London: Springer London, 1999. http://dx.doi.org/10.1007/978-1-4471-0543-5_11.

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Kulikov, Gennady G., and Haydn A. Thompson. "Optimal Control of Gas Turbine Engines Using Mathematical Programming." In Advances in Industrial Control, 251–70. London: Springer London, 2004. http://dx.doi.org/10.1007/978-1-4471-3796-2_14.

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Kurd, Zeshan, and Tim P. Kelly. "Using Safety Critical Artificial Neural Networks in Gas Turbine Aero-Engine Control." In Lecture Notes in Computer Science, 136–50. Berlin, Heidelberg: Springer Berlin Heidelberg, 2005. http://dx.doi.org/10.1007/11563228_11.

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Ganesh, S., P. Chandrasekar, and J. Jayaprabakar. "MHD Flow Measurements of Automatic Control Valve of Gas Turbine Engine Subject to Inclined Magnetic Field." In Recent Advances in Thermofluids and Manufacturing Engineering, 13–21. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-4388-1_2.

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Chasan, David E. "Gas Turbine Engine Lubricants." In Encyclopedia of Tribology, 1460–67. Boston, MA: Springer US, 2013. http://dx.doi.org/10.1007/978-0-387-92897-5_943.

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Liu, Kun, Daifen Chen, Serhiy Serbin, and Volodymyr Patlaichuk. "Gas Turbine Engine Classification." In Gas Turbines Structural Properties, Operation Principles and Design Features, 75–86. Singapore: Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-0977-3_6.

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Conference papers on the topic "Gas Turbine Engine Control"

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Lemmin, Jürgen. "An Approach to an Integrated Control System for a Modern Fighter Aircraft Engine." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-277.

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In the field of today’s military aircraft engines, the engine control system consists in most cases of hydromechanical controls, as such, with an electronic supervisory system. This type of control makes the integration of engine and aircraft systems rather difficult. Even with the Tornado engine which features a full authority electronic engine controller, only initial steps in systems integration are realized. With the introduction of digital electronics into both the engine control and the aircraft systems, together with the availability of data highway systems, large scale systems integration can be envisaged on future fighter aircraft, with the resultant improvement in overall weapon system performance. This paper puts forward a proposal for a control concept for a reheated fighter engine, and outlines possibilities for integration with aircraft systems.
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Watts, J. W., T. E. Dwan, and C. G. Brockus. "Optimal State Space Control of a Gas Turbine Engine." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-219.

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An analog fuel control for a gas turbine engine was compared with several state space derived fuel controls. A single spool, simple cycle gas turbine engine was modeled using ACSL (high level simulation language based on FORTRAN). The model included an analog fuel control representative of existing commercial fuel controls. The ACSL model was stripped of non-essential states to produce an 8 state linear state space model of the engine. The A, B, and C matrices, derived from rated operating conditions, were used to obtain feedback control gains by the following methods: (1) state feedback; (2) LQR theory; (3) Bellman method; and (4) polygonal search. An off-load transient followed by an on-load transient was run for each of these fuel controls. The transient curves obtained were used to compare the state space fuel controls with the analog fuel control. The state space fuel controls did better than the analog control.
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Landy, R. J., W. A. Yonke, and J. F. Stewart. "Development of HIDEC Adaptive Engine Control Systems." In ASME 1986 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1986. http://dx.doi.org/10.1115/86-gt-252.

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The NASA Ames-Dryden Flight Research Facility is sponsoring a flight research program designated Highly Integrated Digital Electronic Control (HIDEC), whose purpose is to develop integrated flight-propulsion control modes and evaluate their benefits in flight on the NASA F-15 test aircraft. The Adaptive Engine Control System (ADECS I) is one phase of the HIDEC program. ADECS I involves uptrimming the P&W Engine Model Derivative (EMD) PW1128 engines to operate at higher engine pressure ratios (EPR) and produce more thrust. In a follow-on phase, called ADECS II, a constant thrust mode will be developed which will significantly reduce turbine operating temperatures and improve thrust specific fuel consumption. A Performance Seeking Control mode is scheduled to be developed. This mode features an onboard model of the engine that will be updated to reflect actual engine performance, accounting for deterioration and manufacturing differences. The onboard engine model, together with inlet and nozzle models, are used to determine optimum control settings for the engine, inlet, and nozzle that will maximize thrust at power settings of intermediate and above and minimize fuel flow at cruise. The HIDEC program phases are described in this paper with particular emphasis on the ADECS I system and its expected performance benefits. The ADECS II and Performance Seeking Control concepts and the plans for implementing these modes in a flight demonstration test aircraft are also described. The potential pay-offs for these HIDEC modes as well as other integrated control modes are also discussed.
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Rodriguez-Vazquez, K. "Multiobjective genetic programming for gas turbine engine model identification." In UKACC International Conference on Control (CONTROL '98). IEE, 1998. http://dx.doi.org/10.1049/cp:19980432.

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Edwards, Jennifer, Frederick Gouldin, and Sandor Becz. "Gas Turbine Engine Combustor Control Using Emission Tomography." In 44th AIAA Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-749.

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Shahriari, A., H. Badihi, and M. Bazazzadeh. "Optimization of a gas turbine engine fuzzy control." In 2012 IEEE Aerospace Conference. IEEE, 2012. http://dx.doi.org/10.1109/aero.2012.6187322.

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Kulkarni, Guruprasad, and Sebastian Price. "MBSE Model on Gas Turbine Tip Clearance Control." In ASME 2019 Gas Turbine India Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gtindia2019-2365.

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Abstract Model Based System Engineering (MBSE) is a systems engineering methodology to understand the customer needs and create functional model to capture requirements and develop design definitions. This paper represents the MBSE activity carried out on Turbine Tip Clearance Control (TCC) System for a Trent XWB Engine. TCC is a critical system of an Aircraft engine, whose function is vital throughout the engine life. This is a complex system as both mechanical and control systems need to interact seamlessly to meet its operational requirement. The key accomplishment of this study is, abstracting of complex mechanical system into functional model and connecting it to functional model of Controls in MBSE environment. This is done for a system that meets the standards of very safety critical and highly regulated industry of Civil Aircraft Engines. The software used for building requirements models for TCC is Capella. Capella is open source free software built on Architecture Analysis and Design Integrated Approach (Arcadia) frame work. This framework extends and simplifies SysML. The advantages of this frame work over SysML are explained in [Ref. 1]. The Arcadia frame work is well suited to capture the complex systems involving multiple disciplines along with Mechanical systems as explained in [Ref. 2]. This paper presents a detailed study performed on product system level requirements and captures both functional and non-functional requirements such as operational and safety requirements. In the Arcadia framework this is represented at system analysis level. Further studies capture the logical and physical architecture which is representative in nature.
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Perez, R. A., and O. D. I. Nwokah. "Full Envelope Multivariable Control of a Gas Turbine Engine." In 1991 American Control Conference. IEEE, 1991. http://dx.doi.org/10.23919/acc.1991.4791472.

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Yonke, W. A., R. J. Landy, and J. F. Stewart. "HIDEC Adaptive Engine Control System Flight Evaluation Results." In ASME 1987 International Gas Turbine Conference and Exhibition. American Society of Mechanical Engineers, 1987. http://dx.doi.org/10.1115/87-gt-257.

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An integrated flight propulsion control mode called Adaptive Engine Control System (ADECS) has been developed and flight demonstrated on an F-15 test aircraft in the Highly Integrated Digital Electronic Control (HIDEC) Program, sponsored by the NASA Ames/Dryden Flight Research Center. The ADECS system provides additional engine thrust by increasing engine pressure ratio (EPR) at intermediate and afterburning power. The amount of EPR uptrim is modulated based on a unique predictor scheme for angle-of-attack and sideslip angle thus ensuring adequate fan stall margin for the engine. These predicted angles are derived from fight control and inertial navigation information. The ADECS mode demonstrated substantial improvements in aircraft and engine performance in the flight evaluation program, even with only one engine incorporating EPR uptrim. Highlights were a 16% rate of climb increase, a 14% reduction in time to climb, and a 15% reduction in time to accelerate. Significant EPR uptrim capability was demonstrated with angles-of-attack up to 20 degrees.
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Culley, Dennis. "Transition in Gas Turbine Control System Architecture: Modular, Distributed, and Embedded." In ASME Turbo Expo 2010: Power for Land, Sea, and Air. ASMEDC, 2010. http://dx.doi.org/10.1115/gt2010-23226.

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Controls systems are an increasingly important component of turbine-engine system technology. However, as engines become more capable, the control system itself becomes ever more constrained by the inherent environmental conditions of the engine; a relationship forced by the continued reliance on commercial electronics technology. A revolutionary change in the architecture of turbine-engine control systems will change this paradigm and result in fully distributed engine control systems. Initially, the revolution will begin with the physical decoupling of the control law processor from the hostile engine environment using a digital communications network and engine-mounted high temperature electronics requiring little or no thermal control. The vision for the evolution of distributed control capability from this initial implementation to fully distributed and embedded control is described in a roadmap and implementation plan. The development of this plan is the result of discussions with government and industry stakeholders.
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Reports on the topic "Gas Turbine Engine Control"

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Crocker, Raju, and Yang. L51796 Document CEM Experience in Natural Gas Transmission Industry. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), March 1999. http://dx.doi.org/10.55274/r0010426.

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Since passage of the 1990 Clean Air Act Amendments (CAAA), continuous emission monitoring system (CEMS) vendors, manufacturers, research organizations, parametric emissions monitoring system (PEMS) vendors, consultants, and source owner/operators have been developing strategies to satisfy compliance monitoring requirements that may eventually apply to many gas turbines and engines. A variety of CEMS and PEMS approaches have been developed, and evaluated to determine overall performance and cost. In addition, a few natural gas transmission companies have been required to install and operate CEMS on specific engines and turbines in order to comply with existing State permitting requirements or emissions trading programs.Within the next five years, the Environmental Protection Agency (EPA) is expected to promulgate a series of stationary source, air emission regulations that will have a significant impact on many industrial sources. In addition, EPA will be issuing regulatory revisions, policy manuals and guidance documents to further clarify the implementation and enforcement of rules recently promulgated - e.g., Title V Permitting, Compliance Assurance Monitoring (CAM) and Credible Evidence rules. As a part of each of these anticipated rules, revisions, and supporting documents, EPA will require and continue to refine corresponding compliance monitoring procedures and performance specifications. For the natural gas transmission industry, the anticipated regulatory changes could result in substantial increases in the cost of environmental compliance. Costs associated with pollution control (including reductions in engine/turbine efficiency), compliance monitoring, emissions reporting and recordkeeping may all increase as a result of pending regulatory requirements. This report has been prepared to document the natural gas transmission industry's experience operating continuous emission monitoring systems (CEMS) on reciprocating engines and stationary gas turbines and to discuss some of the more critical, technical issues that will have to be addressed if pending regulatory changes require the use of CEMS. In particular, this report provides technical discussions regarding the performance, operation, maintenance and costs of a CEMS program for compliance monitoring of nitrogen oxides emissions.
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Thomas, Tucker, and Cowell. PR-283-10204-R01 Prevent Variable Guide Vane Lock-up - Solar Gas Turbines with Intermittent Operation. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), January 2016. http://dx.doi.org/10.55274/r0010856.

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A study was completed to demonstrate that a guide vane field refurbishment process and improved maintenance practices are effective at preventing corrosion and lock-up of the guide vanes of Solar�s Taurus 60-7802S gas turbine operated in intermittent duty. A Taurus 60 engine located at Dominion�s Crayne compressor station was refurbished and operated over a five year period using maintenance practices to slow the build-up of corrosion. The visible condition of the VGV assembly on this Test Unit was monitored and the guide vane actuator force measured to assess if corrosion build-up was occurring. A second co-located Taurus 60 served as a Control Unit to validate that the environment and operating profile were conducive to corrosion build-up. The Control Unit was not modified with the exception that electric actuators were installed on both units so that the VGV actuator force could be measured. The engines logged over 18,000 hours of operation during the test period after which, both units were pulled for overhaul. A detailed inspection and assessment was completed with extensive photographic documentation of the condition of the hardware. The actuator force measured during the start sequence for each of the engines was compared. The Test Unit actuator force varied from 180 to 265 lbf, while the Control Unit had a considerably larger variation of 170 to 315 lbf. The Control Unit suffered a guide vane lock-up event in June of 2014.
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Willson. L51756 State of the Art Intelligent Control for Large Engines. Chantilly, Virginia: Pipeline Research Council International, Inc. (PRCI), September 1996. http://dx.doi.org/10.55274/r0010423.

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Computers have become a vital part of the control of pipeline compressors and compressor stations. For many tasks, computers have helped to improve accuracy, reliability, and safety, and have reduced operating costs. Computers excel at repetitive, precise tasks that humans perform poorly - calculation, measurement, statistical analysis, control, etc. Computers are used to perform these type of precise tasks at compressor stations: engine / turbine speed control, ignition control, horsepower estimation, or control of complicated sequences of events during startup and/or shutdown. For other tasks, however, computers perform very poorly at tasks that humans find to be trivial. A discussion of the differences in the way humans and computer process information is crucial to an understanding of the field of artificial intelligence. In this project, several artificial intelligence/ intelligent control systems were examined: heuristic search techniques, adaptive control, expert systems, fuzzy logic, neural networks, and genetic algorithms. Of these, neural networks showed the most potential for use on large bore engines because of their ability to recognize patterns in incomplete, noisy data. Two sets of experimental tests were conducted to test the predictive capabilities of neural networks. The first involved predicting the ignition timing from combustion pressure histories; the best networks responded within a specified tolerance level 90% to 98.8% of the time. In the second experiment, neural networks were used to predict NOx, A/F ratio, and fuel consumption. NOx prediction accuracy was 91.4%, A/F ratio accuracy was 82.9%, and fuel consumption accuracy was 52.9%. This report documents the assessment of the state of the art of artificial intelligence for application to the monitoring and control of large-bore natural gas engines.
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Korjack, T. A. A Twisted Turbine Blade Analysis for a Gas Turbine Engine. Fort Belvoir, VA: Defense Technical Information Center, August 1997. http://dx.doi.org/10.21236/ada329581.

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Metz, Stephen D., and David L. Smith. Survey of Gas Turbine Control for Application to Marine Gas Turbine Propulsion System Control. Fort Belvoir, VA: Defense Technical Information Center, January 1989. http://dx.doi.org/10.21236/ada204713.

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Cao, Yiding. Miniature Heat Pipe Devices for Gas Turbine Engine Applications. Fort Belvoir, VA: Defense Technical Information Center, December 2002. http://dx.doi.org/10.21236/ada416715.

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Etemad, Shahrokh, Benjamin Baird, Sandeep Alavandi, and William Pfefferle. Industrial Gas Turbine Engine Catalytic Pilot Combustor-Prototype Testing. Office of Scientific and Technical Information (OSTI), April 2010. http://dx.doi.org/10.2172/1051563.

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Roth, P. G. Probabilistic Rotor Design System (PRDS) -- Gas Turbine Engine Design. Fort Belvoir, VA: Defense Technical Information Center, December 1998. http://dx.doi.org/10.21236/ada378908.

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Gregory Corman and Krishan Luthra. Melt Infiltrated Ceramic Composites (Hipercomp) for Gas Turbine Engine Applications. Office of Scientific and Technical Information (OSTI), September 2005. http://dx.doi.org/10.2172/936318.

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Feng, Jinwei, Ricardo Burdisso, Wing Ng, and Ted Rappaport. Turbine Engine Control Using MEMS for Reduction of High Cycle Fatigue. Fort Belvoir, VA: Defense Technical Information Center, March 2001. http://dx.doi.org/10.21236/ada387429.

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