Дисертації з теми "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.
Повний текст джерелаChurchhouse, Stephen Paul. "Multivariable control of a propfan engine." Thesis, University of Cambridge, 1988. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303222.
Повний текст джерелаKeng, W. "Gas turbine engine control and performance enhancement with fuzzy logic." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/11028.
Повний текст джерелаMahmoud, Saad M. "Effective optimal control of a fighter aircraft engine." Thesis, Loughborough University, 1988. https://dspace.lboro.ac.uk/2134/7287.
Повний текст джерелаGomma, 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.
Повний текст джерелаKeng, W. "Gas turbine engine control and performance enchancement with fuzzy logic." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/11028.
Повний текст джерелаChung, 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.
Повний текст джерелаStambaugh, 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.
Повний текст джерелаBae, 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.
Повний текст джерелаVillarreal, Daniel Christopher. "Digital Fuel Control for a Lean Premixed Hydrogen-Fueled Gas Turbine Engine." Thesis, Virginia Tech, 2009. http://hdl.handle.net/10919/34974.
Повний текст джерелаParallel 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
Pakmehr, Mehrdad. "Towards verifiable adaptive control of gas turbine engines." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/49025.
Повний текст джерелаSheldon, Karl Edward. "Analysis Methods to Control Performance Variability and Costs in Turbine Engine Manufacturing." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/32290.
Повний текст джерелаMaster of Science
Haas, David William. "The instrumentation design and control of a T63-A-700 gas turbine engine." Thesis, Monterey, California. Naval Postgraduate School, 1996. http://hdl.handle.net/10945/8538.
Повний текст джерелаGas Turbine Instrumentation and Control
A T63-A-700 gas turbine engine has been instrumented to measure performance parameters. Pressure and temperature monitoring systems have been designed, fabricated, and installed to ensure accurate measurement of performance parameters. All measured parameters have been compared against predicted thermodynamic cycle analysis. Design and control of selected engine systems have been modified to incorporate more precise engine control and safety
McNulty, Gregory Scott. "A study of dynamic compressor surge control strategies for a gas turbine engine." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/47350.
Повний текст джерелаWang, Chen. "Transient performance simulation of gas turbine engine integrated with fuel and control systems." Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/9881.
Повний текст джерелаKamalova, Zukhra. "Dynamic modelling and control of gas turbine engines." Thesis, University of Manchester, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492127.
Повний текст джерелаKorak, Ghosh. "Model predictive control for civil aerospace gas turbine engines." Thesis, University of Sheffield, 2013. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.595827.
Повний текст джерелаAfshari, Seyed Saeed Tavakoli. "Multivariable PID control with application to gas turbine engines." Thesis, University of Sheffield, 2006. http://etheses.whiterose.ac.uk/14882/.
Повний текст джерелаPrashanth, Prakash. "Post-combustion emissions control for aero-gas turbine engines." Thesis, Massachusetts Institute of Technology, 2018. https://hdl.handle.net/1721.1/122402.
Повний текст джерелаCataloged from PDF version of thesis.
Includes bibliographical references (pages 47-50).
Aviation NO[subscript x] emissions have an impact on air quality and climate change, where the latter is magnified due to the higher sensitivity of the upper troposphere and lower stratosphere. In the aviation industry, efforts to increase the efficiency of propulsion systems are giving rise to higher overall pressure ratios which results in higher NO[subscript x] emissions due to increased combustion temperatures. This thesis identifies that the trend towards smaller engine cores (gas generators) that are power dense and contribute little to the thrust output presents new opportunities for emissions control that were previously unthinkable when the core exhaust stream contributed significant thrust. This thesis proposes and assesses selective catalytic reduction (SCR), which is a post-combustion emissions control method used in ground-based sources such as power generation and heavy-duty diesel engines, for use in aero-gas turbines.
The SCR system increases aircraft weight and introduces a pressure drop in the core stream. The effects of these are evaluated using representative engine cycle models provided by a major aero-gas turbine manufacturer. This thesis finds that employing an ammonia-based SCR can achieve close to 95% reduction in NO[subscript x] emissions for ~0.4% increase in block fuel burn. The large size of the catalyst needs to be housed in the body of the aircraft and hence would be suitable for future designs where the engine core is also within the fuselage, such as would be possible with turbo-electric or hybrid-electric designs. The performance of the post-combustion emissions control is shown to improve for smaller core engines in new aircraft in the NASA N+3 time-line (2030-2035), suggesting the potential to further decrease the cost of the ~95% NO[subscript x] reduction to below ~0.4% fuel burn.
Using a global chemistry and transport model (GEOS-Chem) this thesis estimates that using ultra-low sulfur (<15 ppm fuel sulfur content) in tandem with post-combustion emissions control results in a ~92% reduction in annual average population exposure to PM₂.₅ and a ~95% reduction in population exposure to ozone. This averts approximately 93% of the air pollution impact of aviation.
by Prakash Prashanth.
S.M.
S.M. Massachusetts Institute of Technology, Department of Aeronautics and Astronautics
Ekong, Godwin I. "Tip clearance control concepts in gas turbine H.P. compressors." Thesis, University of Sussex, 2014. http://sro.sussex.ac.uk/id/eprint/48906/.
Повний текст джерелаEgener, P. "Design, implementation, and testing of a digital control system for a small gas turbine engine." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 1999. http://www.collectionscanada.ca/obj/s4/f2/dsk1/tape8/PQDD_0006/MQ44840.pdf.
Повний текст джерелаLyes, Peter A. "Low speed axial compressor design and evaluation : High speed representation and endwall flow control studies." Thesis, Cranfield University, 1999. http://hdl.handle.net/1826/4251.
Повний текст джерелаBehrens, Christopher Karl. "An Experimental Investigation into NOx Control of a Gas Turbine Combustor and Augmentor Tube Incorporating a Catalytic Reduction System." Thesis, Monterey, Califonia : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA231427.
Повний текст джерелаThesis Advisor(s): Netzer, D. W. Second Reader: Shreeve, R. P. "March 1990." Description based on signature page as viewed on August 25, 2009. DTIC Descriptor(s): Air, augmentation, catalysis, catalysts, combustors, configurations, engines, fuels, gas generating systems, gas turbines, measurement, pressure, profiles, ratios, reduction, tubes, velocity. DTIC Identifier(s): Nitrogen oxides, NOx control, Gas turbines, Gas analyzers, Pollution abatement, computer programs, Emissions control, Exhaust augmentor tubes, Thesis. Author(s) subject terms: Nox control, gas turbine combustors; emissions control exhaust augmentor tubes; gas analyzers; pollution control. Includes bibliographical references (p. 73-74). Also available online.
Eveker, Kevin M. "Model Development for active control of stall phenomena in aircraft gas turbine engines." Diss., Georgia Institute of Technology, 1993. http://hdl.handle.net/1853/12363.
Повний текст джерелаCornwell, Michael. "Causes of Combustion Instabilities with Passive and Active Methods of Control for practical application to Gas Turbine Engines." University of Cincinnati / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=ucin1307323433.
Повний текст джерелаKaptain, Tyler J. "Hardware Scaled Co-Simulation of Optimal Controlled Hybrid Gas-Electric Propulsion." Cleveland State University / OhioLINK, 2021. http://rave.ohiolink.edu/etdc/view?acc_num=csu1631634390032462.
Повний текст джерелаKratz, Jonathan L. "Robust Control of Uncertain Input-Delayed Sample Data Systems through Optimization of a Robustness Bound." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1429149093.
Повний текст джерелаЄнчев, Сергій Васильович, та Serhii Vasylovych Yenchev. "Синтез інтелектуальних систем керування авіаційними газотурбінними двигунами". Thesis, Національний авіаційний університет, 2020. https://er.nau.edu.ua/handle/NAU/44729.
Повний текст джерелаThe thesis analyses the synthesis of intelligent control systems of aircraft gas turbine engines principles of construction, functions, tasks, methods and algorithms. The thesis studies the structures and information flow in aviation gas turbine engines electronic control systems and establishes the methods and algorithms for identification of aviation gas turbine engines and information processing in the system of automatic control system of gas turbine engines based on intelligent control methods. The study establishes scientific and methodological bases of designing neural network regulators in the structures of intelligent control systems of aviation gas turbine engines: training, synthesis algorithms and settings; intelligent control systems of gas turbine engines formation and intelligent wavelet filter. The method of synthesis of fuzzy intelligent control systems of gas turbine engines using the method of balanced straight line approximation and algorithmic maintenance of their functioning is developed. The thesis proposes the concept of intelligent control systems of gas turbine engines optimization in terms of system approach. The control part of the systems is a single mathematical operator that converts input information into control effects. The study provides the method and methodology for the intelligent control systems of the gas turbine engine control laws optimization in the course of operation in stable and transient modes according to the criteria: speed, minimum fuel consumption, based on the abovementioned concept. The thesis offers the solution to the problem of failure-resistant control algorithms synthesis of intelligent control systems of gas turbine engines on the basis of fuzzy logic and neural networks. The algorithm and method for the synthesis of neural network regulator as a part of intelligent control systems of gas turbine engines are developed. The study analyses the dependence of intelligent control systems management quality on the choice of neuron network architecture and structure. The failure-resistance algorithm for intelligent control systems of gas turbine engines is proposed. The algorithm is based on the use of FDI method, characterized in that the detection of failures in the system is carried out by comparing elements of intelligent control systems of gas turbine engines with the elements of the reference neural network model of intelligent control systems. The reference model is used in real-time mode. Therefore, the reliability of the failures detection in a wide work and characteristics variation range of intelligent control systems of gas turbine engines.
Ismail, Ibrahim H. "Simulation of aircraft gas turbine engine." Thesis, University of Hertfordshire, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.303465.
Повний текст джерелаFarahani, Arash. "Gas turbine engine static strip seals." Thesis, University of Sussex, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.444118.
Повний текст джерелаKashinath, Karthik. "Nonlinear thermoacoustic oscillations of a ducted laminar premixed flame." Thesis, University of Cambridge, 2013. https://www.repository.cam.ac.uk/handle/1810/264291.
Повний текст джерелаSiddiqi, Majid. "Turbine Engine Control and Diagnostics." The Ohio State University, 2005. http://rave.ohiolink.edu/etdc/view?acc_num=osu1420210543.
Повний текст джерелаZedda, M. "Gas turbine engine and sensor fault diagnosis." Thesis, Cranfield University, 1999. http://dspace.lib.cranfield.ac.uk/handle/1826/9117.
Повний текст джерелаSingh, Grewal M. "Gas Turbine Engine Performance Deterioration Modelling and Analysis." Thesis, Cranfield University, 1988. http://dspace.lib.cranfield.ac.uk/handle/1826/8068.
Повний текст джерелаRoth, Richard. "Materials substitution in aircraft gas turbine engine applications." Thesis, Massachusetts Institute of Technology, 1992. http://hdl.handle.net/1721.1/13112.
Повний текст джерелаNishimoto, Keane T. (Keane Takeshi) 1981. "Design of an automobile turbocharger gas turbine engine." Thesis, Massachusetts Institute of Technology, 2003. http://hdl.handle.net/1721.1/41810.
Повний текст джерелаIncludes bibliographical references (leaf 24).
The turbocharger gas turbine engine was designed with the intent of being built as a demonstration for the Massachusetts Institute of Technology Department of Mechanical Engineering courses 2.005 and 2.006 to supplement material covered. A gas turbine operates on an open version of the Brayton cycle and consists of a compressor, a combustion chamber and a turbine. An automobile turbocharger was chosen because it contains a compressor and turbine on a common shaft. Designs for the combustion chamber, oil system, fuel system, and ignition system were created based on research of similar projects. Many of the necessary parts were also specified.
by Keane T. Nishimoto.
S.B.
Moy, Habs M. (Habs Mern) 1967. "Commercial gas turbine engine platform strategy and design." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/88328.
Повний текст джерелаGulati, Ankush. "An optimization tool for gas turbine engine diagnostics." Thesis, Cranfield University, 2001. http://dspace.lib.cranfield.ac.uk/handle/1826/10699.
Повний текст джерелаNikolaidis, Theoklis. "Water ingestion effects on gas turbine engine performance." Thesis, Cranfield University, 2008. http://hdl.handle.net/1826/3516.
Повний текст джерелаStitzel, Sarah M. "Flow Field Computations of Combustor-Turbine Interactions in a Gas Turbine Engine." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/30992.
Повний текст джерелаMaster of Science
Poppe, Christian. "Scalar measurements in a gas turbine combustor." Thesis, Imperial College London, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.264987.
Повний текст джерелаGroshenry, Christophe. "Preliminary design study of a micro-gas turbine engine." Thesis, Massachusetts Institute of Technology, 1995. http://hdl.handle.net/1721.1/10386.
Повний текст джерелаLiu, Chunmeni 1970. "Dynamical system modeling of a micro gas turbine engine." Thesis, Massachusetts Institute of Technology, 2000. http://hdl.handle.net/1721.1/9249.
Повний текст джерелаAlso available online at the MIT Theses Online homepage
Includes bibliographical references (p. 123).
Since 1995, MIT has been developing the technology for a micro gas turbine engine capable of producing tens of watts of power in a package less than one cubic centimeter in volume. The demo engine developed for this research has low and diabtic component performance and severe heat transfer from the turbine side to the compressor side. The goals of this thesis are developing a dynamical model and providing a simulation platform for predicting the microengine performance and control design, as well as giving an estimate of the microengine behavior under current design. The thesis first analyzes and models the dynamical components of the microengine. Then a nonlinear model, a linearized model, and corresponding simulators are derived, which are valid for estimating both the steady state and transient behavior. Simulations are also performed to estimate the microengine performance, which include steady states, linear properties, transient behavior, and sensor options. A parameter study and investigation of the startup process are also performed. Analysis and simulations show that there is the possibility of increasing turbine inlet temperature with decreasing fuel flow rate in some regions. Because of the severe heat transfer and this turbine inlet temperature trend, the microengine system behaves like a second-order system with low damping and poor linear properties. This increases the possibility of surge, over-temperature and over-speed. This also implies a potentially complex control system. The surge margin at the design point is large, but accelerating directly from minimum speed to 100% speed still causes surge. Investigation of the sensor options shows that temperature sensors have relatively fast response time but give multiple estimates of the engine state. Pressure sensors have relatively slow response time but they change monotonically with the engine state. So the future choice of sensors may be some combinations of the two. For the purpose of feedback control, the system is observable from speed, temperature, or pressure measurements. Parameter studies show that the engine performance doesn't change significantly with changes in either nozzle area or the coefficient relating heat flux to compressor efficiency. It does depend strongly on the coefficient relating heat flux to compressor pressure ratio. The value of the compressor peak efficiency affects the engine operation only when it is inside the range of the engine operation. Finally, parameter studies indicate that, to obtain improved transient behavior with less possibility of surge, over-temperature and over-speed, and to simplify the system analysis and design as well as the design and implementation of control laws, it is desirable to reduce the ratio of rotor mechanical inertia to thermal inertia, e.g. by slowing the thermal dynamics. This can in some cases decouple the dynamics of rotor acceleration and heat transfer. Several methods were shown to improve the startup process: higher start speed, higher start spool temperature, and higher start fuel flow input. Simulations also show that the efficiency gradient affects the transient behavior of the engine significantly, thereby effecting the startup process. Finally, the analysis and modeling methodologies presented in this thesis can be applied to other engines with severe heat transfer. The estimates of the engine performance can serve as a reference of similar engines as well.
by Chunmei Liu.
S.M.
Savoulides, Nicholas 1978. "Development of a MEMS turbocharger and gas turbine engine." Thesis, Massachusetts Institute of Technology, 2004. http://hdl.handle.net/1721.1/17815.
Повний текст джерелаIncludes bibliographical references.
As portable electronic devices proliferate (laptops, GPS, radios etc.), the demand for compact energy sources to power them increases. Primary (non-rechargeable) batteries now provide energy densities upwards of 180 W-hr/kg, secondary (rechargeable) batteries offer about 1/2 that level. Hydrocarbon fuels have a chemical energy density of 13,000-14,000 W-hr/kg. A power source using hydrocarbon fuels with an electric power conversion efficiency of order 10% would be revolutionary. This promise has driven the development of the MIT micro gas turbine generator concept. The first engine design measures 23 x 23 x 0.3 mm and is fabricated from single crystal silicon using MEMS micro-fabrication techniques so as to offer the promise of low cost in large production. This thesis describes the development and testing of a MEMS turbocharger. This is a version of a simple cycle, single spool gas turbine engine with compressor and turbine flow paths separated for diagnostic purposes, intended for turbomachinery and rotordynamic development. The turbocharger design described herein was evolved from an earlier, unsuccessful design (Protz 2000) to satisfy rotordynamic and fabrication constraints. The turbochargers consist of a back-to-back centrifugal compressor and radial inflow turbine supported on gas bearings with a design rotating speed of 1.2 Mrpm. This design speed is many times the natural frequency of the radial bearing system. Primarily due to the exacting requirements of the micron scale bearings, these devices have proven very difficult to manufacture to design, with only six near specification units produced over the course of three years. Six proved to be a small number for this development program since these silicon devices are brittle
(cont.) and do not survive bearing crashes at speeds much above a few tens of thousands of rpm. The primary focus of this thesis has been the theoretical and empirical determination of strategies for the starting and acceleration of the turbocharger and engine and evolution of the design to that end. Experiments identified phenomena governing rotordynamics, which were compared to model predictions. During these tests, the turbocharger reached 40% design speed (480,000 rpm). Rotordynamics were the limiting factor. The turbomachinery performance was characterized during these experiments. At 40% design speed, the compressor developed a pressure ratio of 1.21 at a flow rate of 0.13 g/s, values in agreement with CFD predictions. At this operating point the turbine pressure ratio was 1.7 with a flow rate of 0.26 g/s resulting in an overall spool efficiency of 19%. To assess ignition strategies for the gas turbine, a lumped parameter model was developed to examine the transient behavior of the engine as dictated by the turbomachinery fluid mechanics, heat transfer, structural deformations from centrifugal and thermal loading and rotordynamics. The model shows that transients are dominated by three time constants - rotor inertial (10⁻¹ sec), rotor thermal (lsec), and static structure thermal (10sec). The model suggests that the engine requires modified bearing dimensions relative to the turbocharger and that it might be necessary to pre-heat the structure prior to ignition ...
by Nicholas Savoulides.
Ph.D.
Hancock, Simon David. "Gas turbine engine controller design using multi-objective optimization techniques." Thesis, Bangor University, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.304616.
Повний текст джерелаASSUMPCAO, VICTOR DOS SANTOS. "CONTROL STRATEGY OF A GAS TURBINE." PONTIFÍCIA UNIVERSIDADE CATÓLICA DO RIO DE JANEIRO, 2012. http://www.maxwell.vrac.puc-rio.br/Busca_etds.php?strSecao=resultado&nrSeq=21016@1.
Повний текст джерелаApós um período de baixa nas bacias hidrográficas, o Brasil investiu em novas fontes de geração de energia elétrica. O gás natural é um dos exemplos destas novas fontes de energia. Dentre as usinas usuárias deste combustível, existem aquelas que operam com turbinas a gás. Muitos estudos sobre modelagem de turbinas a gás, simulação de desempenho, diagnóstico e controle começaram devido a importância dessas usinas. Assim, torna-se necessário que estas usinas trabalhem com segurança e confiabilidade. Para garantir esta estabilidade, é necessário o desenvolvimento de um sistema de controle, capaz de realizar esta operação de geração de energia elétrica de forma satisfatória. O sistema de controle utilizado por estes equipamentos é o objeto de estudo deste trabalho. Neste trabalho, foi utilizado um modelo computacional de uma turbina a gás com duas características principais: um modelo computacional do sistema de controle, desenvolvido com base em uma nova metodologia de controle de turbina a gás, e um modelo termodinâmico existente de uma turbina a gás ligado à rede brasileira. O sistema de controle utiliza a temperatura de saída da turbina a gás (TET), como um fator de correção, para ajustar a temperatura da entrada da turbina (TIT). Esta temperatura (TIT) é utilizada como referência para o controle de fluxo de combustível injetado no interior da câmara de combustão. O modelo também controla o VIGV (pás diretoras móveis na entrada do compressor) através de uma curva utilizada no controle desta turbina a gás ligada à rede brasileira. O modelo computacional ainda apresenta um cálculo simplificado da composição molar dos gases de exaustão desta máquina térmica. Esta característica pode ser usada em combinação com um modelo de uma caldeira de recuperação de calor (HRSG), para simular uma condição de queima suplementar (duct burner), onde o principal objetivo é aumentar a potência produzida no ciclo. Os resultados da simulação foram comparados com os dados operacionais da usina brasileira.
After a period of water shortage, Brazil invested in new sources of electricity generation. Natural gas is an example of these new energy sources. Among these plants, some operate with gas turbines. Many studies about gas turbine modeling, performance´s simulation, diagnosis and control have started due the importance of these power plants. Thus, it is necessary that these plants work safely and reliably. To ensure this stability, it is necessary to develop a control system capable of performing this operation for generating electricity in a satisfactory manner. Then, the control system used by this equipment becomes the objective of this study. In this work, a computational model of a gas turbine was used with two main features: a developed computational model of control system based on a new methodology of gas turbine control and an existing thermodynamic model of a gas turbine connected to the Brazilian grid. The control system uses the turbine exhaust temperature (TET) as a corrective factor to adjust the turbine inlet temperature (TIT). TIT was used as a setpoint to control the fuel flow injected inside the combustor. The model also controls the IGV (Inlet Guide Vanes) by a control curve used in control of a specific gas turbine. There is a simplified calculation of the molar composition of the exhaust gas. This feature could be used in combination with a model of a heat recovery steam generator (HRSG) to simulate a condition with duct burners where the main objective is increase the cycle power. The results of simulation were compared to the operational data from the Brazilian power plant.
Boumedmed, Abdelkader. "The use of variable engine geometry to improve the transient performance of a two-spool turbofan engine." Thesis, University of Glasgow, 1997. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.263451.
Повний текст джерелаLee, Y. H. "Gas turbine engine health monitoring by fault pattern matching method." Thesis, Cranfield University, 1998. http://dspace.lib.cranfield.ac.uk/handle/1826/10714.
Повний текст джерелаJoo, Won-Gu. "Intake/engine flowfield coupling in turbofan engines." Thesis, University of Cambridge, 1994. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.319865.
Повний текст джерелаBurgess, C. A. R. "The application of aero gas turbine engine monitoring systems to military aircraft." Thesis, Cranfield University, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.232816.
Повний текст джерела