Steady and Transient Performance Prediction of Gas Turbine Engines PDF Download
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Languages : en
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Author:
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Languages : en
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Author: North Atlantic Treaty Organization. Advisory Group for Aeronautical Research and Development
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Languages : en
Pages :
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Category :
Languages : en
Pages : 192
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This Lecture Series covers topics of aero-thermodynamic performance prediction methods for gas turbine engines with respect to steady and transient operation. This includes advanced cycle calculation methods, also taking into account variable cycle engine types. A very important objective is the consideration of installation effects, i.e. Reynolds number and inlet distortions, as well as advanced control concepts for increasing engine surge margins. In addition to these topics, individual papers include practical considerations in designing the engine cycle, dynamic simulation, inlet distortion effects in aircraft propulsion system integration, smart engines, performance and health monitoring models. This Lecture Series, sponsored by the Propulsion and Energetics Panel of AGARD, has been implemented by the Consultant and Exchange Programme. Aerothermodynamics, Predictions, Gas turbine engines, Computerized.
Author: Bhavik Mody
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Languages : en
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The research study focuses on the idea of simulation of an Integrated FullElectric Propulsion System. The simulation required the development of a gasturbine performance model that could predict the dynamic behaviour of theengine in response to a fluctuation of electrical load. For this purposes it wasnecessary to evaluate the thermodynamic working process of the gas turbineand a computer code was created. A design point model written in FORTRAN77 had been transformed to predict the steady state and transientperformance of a two-shaft gas turbine and single shaft gas turbine. Themodels were based on the thermodynamic law of conservation of mass. Forthe model of the two-shaft gas turbine controls system equations had beenderived from off-design analysis and implemented as handles for operation. Both the models were then transformed to a direct link library for theSIMULINK? package. They were further implemented with an electricalnetwork model to form a high-fidelity prime mover-electrical networkpropulsiondrive interface with which a complete systems analysis was doneto understand the response of the three systems in parallel. In a second part heat exchanger modelling had to be performed so as tocreate a gas turbine model of an intercooled-recuperated engine. This wasdone for the steady state behaviour and sizing problem of heat exchangers. The models were run parallel to the steady state code as a validationexercise. Due to time and project restraints the complete incorporation of themodels with the gas turbine code was not performed and only a uni-directionalsystem of heat exchanger was created. Over all the period of researchparametric studies had been done for comparison of various aspects ofperformance. The high fidelity model of the prime mover-electrical network highlighted thereasons for studying the impact of the propulsion drive and electrical networkload dynamics on the operation of the prime movers and vice versa. The loss-of-propulsion-load scenario case study has demonstrated the capabilities ofthe integrated model, showing clear interactions between the individualsubsystems. The interface can now be used to analyse novel types of gasturbine engines in the future. The method adopted to simulate transientperformance of gas turbines was useful in understanding the impact of bleedair on current and novel cycles. Finally the task of heat exchanger simulationemphasized the need to create better and accurate models to understand theimpact of its behaviour on the gas turbine.
Author: H. I. H. Saravanamuttoo
Publisher:
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Category :
Languages : en
Pages : 17
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Book Description
The lecture outlines the basic methods of component matching which are central to the prediction of gas turbine performance. Steady state prediction of off-design performance must be done at the beginning of an engine development program, to ensure that the engine can satisfy all the mission requirements. The matching techniques can be extended to predict transient performance, which is essential for controls development and to ensure good engine handling. The large amount of computation required demands the use of computer modelling and the role of modelling in the development program and the basic requirements for performance modelling are described.
Author:
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Category :
Languages : en
Pages : 651
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Book Description
A Technical Team of the NATO RTO has created a report on gas turbine simulation, ranging from applications to latest methodology of modeling techniques for gas turbine propulsion applications. The report includes examples of how gas turbine numerical simulations have been utilized for aircraft, marine, and vehicular propulsion applications. The major numerical simulation presented in the report is the gas turbine engine cycle code which provides performance for both steady state and transient operation. In addition to examples of how cycle codes are used, an in-depth discussion of how cycle codes are constructed and what basic assumptions are involved is given in the report. Additional higher order and specific numerical simulations for component design and operation are presented in the appendices to this report. Present computer platforms in use for such models are reviewed, and an outlook on development is given. The report aims at increasing the use and the value of engine computer simulations in NATO Nations and NATO's design and use of engines.
Author: S-15 Gas Turbine Perf Simulation Nomenclature and Interfaces
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Category :
Languages : en
Pages : 0
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This Aerospace Standard (AS) provides the method for presentation of gas turbine engine steady-state and transient performance calculated using digital computer programs. It also provides for the presentation of parametric gas turbine data including performance, weight and dimensions computed by digital computer programs.This standard is intended to facilitate calculations by the program user without unduly restricting the method of calculation used by the program supplier.
Author:
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Category : Aeronautics
Languages : en
Pages : 892
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Category :
Languages : en
Pages : 30
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Author: Hanz Richter
Publisher: Springer Science & Business Media
ISBN: 1461411718
Category : Technology & Engineering
Languages : en
Pages : 275
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Book Description
Advanced Control of Turbofan Engines describes the operational performance requirements of turbofan (commercial) engines from a controls systems perspective, covering industry-standard methods and research-edge advances. This book allows the reader to design controllers and produce realistic simulations using public-domain software like CMAPSS: Commercial Modular Aero-Propulsion System Simulation, whose versions are released to the public by NASA. The scope of the book is centered on the design of thrust controllers for both steady flight and transient maneuvers. Classical control theory is not dwelled on, but instead an introduction to general undergraduate control techniques is provided. Advanced Control of Turbofan Engines is ideal for graduate students doing research in aircraft engine control and non-aerospace oriented control engineers who need an introduction to the field.
