Computational Simulation of Gas Turbines: Part 2—Extensible Domain Framework

2000 ◽  
Vol 122 (3) ◽  
pp. 377-386 ◽  
Author(s):  
John A. Reed ◽  
Abdollah A. Afjeh
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Design Patterns ◽  
Heterogeneous Computing ◽  
Computational Simulation ◽  
Object Oriented ◽  
Turbine Engine ◽  
Engine Model ◽  
Computationally Intensive ◽  
High Level

This paper describes the design concepts and object-oriented architecture of Onyx, an extensible domain framework for computational simulation of gas turbine engines. Onyx provides a flexible environment for defining, modifying, and simulating the component-based gas turbine models described in Part 1 of this paper. Using advanced object-oriented technologies such as design patterns and frameworks, Onyx enables users to customize and extend the framework to add new functionality or adapt simulation behavior as required. A customizable visual interface provides high-level symbolic control of propulsion system construction and execution. For computationally-intensive analysis, components may be distributed across heterogeneous computing architectures and operating systems. A distributed gas turbine engine model is developed and simulated to illustrate the use of the framework. [S0742-4795(00)02403-0]

scholarly journals Computational Simulation of Gas Turbines: Part II — Extensible Domain Framework

1999 ◽  
Author(s):  
John A. Reed ◽  
Abdollah A. Afjeh
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Design Patterns ◽  
Heterogeneous Computing ◽  
Computational Simulation ◽  
Object Oriented ◽  
Turbine Engine ◽  
Engine Model ◽  
Computationally Intensive ◽  
High Level

This paper describes the design concepts and object-oriented architecture of Onyx, an extensible domain framework for computational simulation of gas turbine engines. Onyx provides a flexible environment for defining, modifying and simulating the component-based gas turbine models described in Part 1 of this paper. Using advanced object-oriented technologies such as design patterns and frameworks, Onyx enables users to customize and extend the framework to add new functionality or adapt simulation behavior as required. A customizable visual interface provides high-level symbolic control of propulsion system construction and execution. For computationally-intensive analysis, components may be distributed across heterogeneous computing architectures and operating systems. A distributed gas turbine engine model is developed and simulated to illustrate the use of the framework.

scholarly journals Computational Simulation of Gas Turbines: Part I — Foundations of Component-Based Models

1999 ◽  
Author(s):  
John A. Reed ◽  
Abdollah A. Afjeh
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Computational Simulation ◽  
Simulation Models ◽  
Engineering Model ◽  
Levels Of Abstraction ◽  
Turbine Engine ◽  
Engine Model ◽  
Flexible Component ◽  
Aerospace Propulsion

Designing and developing new aerospace propulsion systems is time-consuming and expensive. Computational simulation is a promising means for alleviating this cost, but requires a flexible software simulation system capable of integrating advanced multidisciplinary and multifidelity analysis methods, dynamically constructing arbitrary simulation models, and distributing computationally complex tasks. To address these issues, we have developed Onyx, a Java-based object-oriented domain framework for aerospace propulsion system simulation. This paper presents the design of a common engineering model formalism for use in Onyx. This approach, which is based on hierarchical decomposition and standardized interfaces, provides a flexible component-based representation for gas turbine systems, subsystems and components. It allows new models to be composed programmatically or visually to form more complex models. Onyx’s common engineering model also supports integration of a hierarchy of models which represent the system at differing levels of abstraction. Selection of a particular model is based on a number of criteria, including the level of detail needed, the objective of the simulation, the available knowledge, and given resources. The common engineering model approach is demonstrated by developing gas turbine component models which will be used to compose a gas turbine engine model in Part II of this paper.

Computational Simulation of Gas Turbines: Part 1—Foundations of Component-Based Models

2000 ◽  
Vol 122 (3) ◽  
pp. 366-376 ◽  
Author(s):  
John A. Reed ◽  
Abdollah A. Afjeh
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Computational Simulation ◽  
Simulation Models ◽  
Engineering Model ◽  
Levels Of Abstraction ◽  
Turbine Engine ◽  
Engine Model ◽  
Flexible Component ◽  
Aerospace Propulsion

Designing and developing new aerospace propulsion systems is time-consuming and expensive. Computational simulation is a promising means for alleviating this cost, but requires a flexible software simulation system capable of integrating advanced multidisciplinary and multifidelity analysis methods, dynamically constructing arbitrary simulation models, and distributing computationally complex tasks. To address these issues, we have developed Onyx, a Java-based object-oriented domain framework for aerospace propulsion system simulation. This paper presents the design of a common engineering model formalism for use in Onyx. This approach, which is based on hierarchical decomposition and standardized interfaces, provides a flexible component-based representation for gas turbine systems, subsystems and components. It allows new models to be composed programmatically or visually to form more complex models. Onyx’s common engineering model also supports integration of a hierarchy of models which represent the system at differing levels of abstraction. Selection of a particular model is based on a number of criteria, including the level of detail needed, the objective of the simulation, the available knowledge, and given resources. The common engineering model approach is demonstrated by developing gas turbine component models which will be used to compose a gas turbine engine model in Part 2 of this paper. [S0742-4795(00)02303-6]

GSP, a Generic Object-Oriented Gas Turbine Simulation Environment

2000 ◽  
Author(s):  
Wilfried P. J. Visser ◽  
Michael J. Broomhead
Keyword(s):  
Performance Analysis ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Engine Performance ◽  
Object Oriented ◽  
Control Logic ◽  
Turbine Engine ◽  
Industrial Gas Turbines ◽  
On Line ◽  
Turboshaft Engine

NLR’s primary tool for gas turbine engine performance analysis is the ‘Gas turbine Simulation Program’ (GSP), a component based modeling environment. GSP’s flexible object-oriented architecture allows steady-state and transient simulation of any gas turbine configuration using a user-friendly drag&drop interface with on-line help running under Windows95/98/NT. GSP has been used for a variety of applications such as various types of off-design performance analysis, emission calculations, control system design and diagnostics of both aircraft and industrial gas turbines. More advanced applications include analysis of recuperated turboshaft engine performance, lift-fan STOVL propulsion systems, control logic validation and analysis of thermal load calculation for hot section life consumption modeling. In this paper the GSP modeling system and object-oriented architecture are described. Examples of applications for both aircraft and industrial gas turbine performance analysis are presented.

Cycle Optimisation Using an Advanced, Real Engine Performance Prediction Model

2002 ◽  
Author(s):  
Miles Coppinger ◽  
Graham Cox ◽  
John Hannis ◽  
Nigel Cox
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Engine Performance ◽  
Integer Number ◽  
Turbine Engine ◽  
Engine Model ◽  
Engine Design ◽  
Industrial Gas Turbines ◽  
High Degree ◽  
Technology Level

A whole gas-turbine engine model has been developed incorporating all of the key turbomachinery aerothermal relationships. The aim of the model has been to predict trends in gas-turbine performance with a high degree of confidence that they reflect real engine design limitations. Simple cycles, recuperated, inter-cooled, and inter-cooled recuperated cycles can be assessed across a wide of range of operating parameters. The model is spreadsheet-based with additional macro programming. The major part of it is concerned with establishing representative overall turbine characteristics. A non-integer number of stages is determined as a function of technology level inputs. Individual stage geometry features are derived allowing the calculation of the coolant requirements and efficiencies. The results of various studies are presented for a number of cycle types. The resulting trends are believed to be sensible because of the realistic turbine features. Confidence in the method is established by the modelling of a number of existing industrial gas turbines.

A Model-Based Controller for Commercial Aero Gas Turbines

2002 ◽  
Author(s):  
Arkadiy Turevskiy ◽  
Richard Meisner ◽  
Robert H. Luppold ◽  
Ronald A. Kern ◽  
James W. Fuller
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Gas Turbines ◽  
Controller Design ◽  
Control Loop ◽  
Turbine Engine ◽  
Model Based Control ◽  
Engine Model ◽  
Model Based ◽  
Loop Feedback

This article describes the design and development of a model-based control system for a large commercial aero gas turbine engine. The control system, referred to as the Integrated Margin Management (IMM) control, exploits a real-time engine model (RTEM) to estimate control loop feedback signals, enabling the implementation of nontraditional control modes. These nontraditional control modes include algorithms for controlling, optimizing, and/or trading off margins to key operational limits such as thrust, compressor stability, combustor stability, turbine life, redline limits, and emissions. An overview of the results produced with the IMM controller design illustrates the feasibility of this approach for commercial aero gas turbine applications.

Design, Development and Application of Vehicle Gas Turbine Engines

1966 ◽  
Vol 181 (1) ◽  
pp. 149-172
Author(s):  
P. A. Phillips ◽  
Peter Spear
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Low Cost ◽  
Engine Performance ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Design Development ◽  
Turbine Engine ◽  
Wide Range ◽  
Cycle Temperature

After briefly summarizing worldwide automotive gas turbine activity, the paper analyses the power plant requirements of a wide range of vehicle applications in order to formulate the design criteria for acceptable vehicle gas turbines. Ample data are available on the thermodynamic merits of various gas turbine cycles; however, the low cost of its piston engine competitor tends to eliminate all but the simplest cycles from vehicle gas turbine considerations. In order to improve the part load fuel economy, some complexity is inevitable, but this is limited to the addition of a glass ceramic regenerator in the 150 b.h.p. engine which is described in some detail. The alternative further complications necessary to achieve satisfactory vehicle response at various power/weight ratios are examined. Further improvement in engine performance will come by increasing the maximum cycle temperature. This can be achieved at lower cost by the extension of the use of ceramics. The paper is intended to stimulate the design application of the gas turbine engine.

Combustion Technology for Low-Emissions Gas-Turbines: Some Recent Modeling Results

1996 ◽  
Vol 118 (3) ◽  
pp. 201-208 ◽  
Author(s):  
S. M. Correa ◽  
I. Z. Hu ◽  
A. K. Tolpadi
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Spectroscopic Data ◽  
Physical Models ◽  
Gas Turbine Combustor ◽  
Finite Rate ◽  
Recent Developments ◽  
Combustion Technology ◽  
Computationally Intensive ◽  
Transport Method

Computer modeling of low-emissions gas-turbine combustors requires inclusion of finite-rate chemistry and its intractions with turbulence. The purpose of this review is to outline some recent developments in and applications of the physical models of combusting flows. The models reviewed included the sophisticated and computationally intensive velocity-composition pdf transport method, with applications shown for both a laboratory flame and for a practical gas-turbine combustor, as well as a new and computationally fast PSR-microstructure-based method, with applications shown for both premixed and nonpremixed flames. Calculations are compared with laserbased spectroscopic data where available. The review concentrates on natural-gas-fueled machines, and liquid-fueled machines operating at high power, such that spray vaporization effects can be neglected. Radiation and heat transfer is also outside the scope of this review.

Future Vehicular Recuperator Technology Projections

1994 ◽  
Author(s):  
Robert A. Wilson ◽  
Daniel B. Kupratis ◽  
Satyanarayana Kodali
Keyword(s):  
Gas Turbine ◽  
Fuel Economy ◽  
Department Of Defense ◽  
Gas Turbines ◽  
High Performance ◽  
Development Program ◽  
Turn Of The Century ◽  
Turbine Engine ◽  
Technology Roadmap ◽  
Vehicle Propulsion

The Department of Defense and NASA have funded a major gas turbine development program, Integrated High Performance Turbine Engine Technology (IHPTET), to double the power density and fuel economy of gas turbines by the turn of the century. Seven major US gas turbine developers participated in this program. While the focus of IHPTET activity has been aircraft propulsion, the same underlying technology can be applied to water craft and terrestrial vehicle propulsion applications, such as the future main battle tank. For these applications, the gas turbines must be equipped with recuperators. Currently, there is no technology roadmap or set of goals to guide industry and government in the development of a next generation recuperator for such applications.

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