Simulation of Aircraft Gas Turbine Engines

1991 ◽  
Vol 113 (1) ◽  
pp. 95-99 ◽  
Author(s):  
I. H. Ismail ◽  
F. S. Bhinder
Keyword(s):  
Steady State ◽  
Computer Program ◽  
Gas Turbine ◽  
Performance Characteristics ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Steady State Operation

The paper describes a computer program to simulate aircraft gas turbine engines. The program has been written for IBM-compatible microcomputers and is modular in its appraoch. Either analytical equations or detailed performance characteristics of individual components are used to model the steady-state operation of the complete engine.

scholarly journals Simulation of Aircraft Gas Turbine Engines

1990 ◽  
Author(s):  
I. H. Ismail ◽  
F. S. Bhinder
Keyword(s):  
Steady State ◽  
Computer Program ◽  
Gas Turbine ◽  
Performance Characteristics ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Steady State Operation

The paper describes a computer program to simulate aircraft gas turbine engines. The program has been written for IBM compatible micro computers and is modular in its approach. Either analytical equations or detailed performance characteristics of individual components are used to model the steady state operation of the complete engine.

scholarly journals A Software Environment for the Modelling, Simulation and Control of Industrial Gas Turbine Engines

1991 ◽  
Author(s):  
C. Poole ◽  
A. G. Salsi ◽  
F. S. Bhinder ◽  
S. Kumar
Keyword(s):  
Computer Program ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Software Environment ◽  
Turbine Engine ◽  
Simulation And Control ◽  
Industrial Gas Turbine ◽  
And Control ◽  
Modelling Simulation

This paper describes a computer program which has been developed to simulate industrial gas turbine engines to aid the design and application of fuel controllers. It explains the program structure and, as an example, gives the application of the program to the modelling of a simple two shaft industrial gas turbine engine. A brief discussion of the value of the implementation language, C++, is also given.

scholarly journals A Chambered Porous Damper for Rotor Vibration Control: Part II — Imbalance Response and Bladeloss Simulation

1991 ◽  
Author(s):  
J. Walton ◽  
M. Martin
Keyword(s):  
Steady State ◽  
Gas Turbine ◽  
Squeeze Film ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Wide Range ◽  
Squeeze Film Dampers ◽  
Damper Design ◽  
Control Part

In this paper, results of experimental rotordynamic evaluations of a novel, high load chambered porous damper design, are presented. The chambered porous damper concept was evaluated for gas turbine engine application since this concept avoids the non-linearities associated with high eccentricity operation of conventional squeeze film dampers. The rotordynamic testing was conducted under large steady state imbalance and simulated transient bladeloss conditions for up to 0.254 mm (0.01 in) mass c.g offset or 180 gm-cm (2.5 oz-in) imbalance. The chambered porous damper demonstrated that the steady state imbalance and simulated bladeloss transient response of a flexible rotor operating above its first bending critical speed could be readily controlled. Rotor system imbalance sensitivity and logarithmic decrement are presented showing the characteristics of the system with the damper installed. The ability to accommodate high steady state and transient imbalance conditions make this damper well suited to a wide range of rotating machinery, including aircraft gas turbine engines.

Performance Characteristics of Brush Seals for Limited-Life Engines

1993 ◽  
Vol 115 (2) ◽  
pp. 390-396 ◽  
Author(s):  
R. E. Chupp ◽  
C. A. Dowler
Keyword(s):  
Gas Turbine ◽  
Engine Performance ◽  
Performance Characteristics ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Labyrinth Seals ◽  
Performance Improvements ◽  
Limited Life ◽  
In Series ◽  
Brush Seals

Brush seals are potential replacements for air-to-air labyrinth seals in gas turbine engines. An investigation has been conducted to determine the performance characteristics of brush seals for application in limited-life gas turbine engines. An elevated temperature, rotating test rig was designed and built to test labyrinth and brush seals in simulated subsonic and supersonic engine conditions. Results from initial tests for subsonic applications demonstrated that brush seals exhibit appreciably lower leakage compared to labyrinth seals, and thus offer significant engine performance improvements. Performance results have been obtained showing the effect of various brush seal parameters, including: initial interference, backplate gap, and multiple brush seals in series.

scholarly journals Transient Dynamics of Gas Turbine Engines

1993 ◽  
Author(s):  
A. R. Ganji ◽  
M. Khadem ◽  
S. M. H. Khandani
Keyword(s):  
Steady State ◽  
Differential Equations ◽  
Gas Turbine ◽  
Initial Conditions ◽  
Transient Behavior ◽  
Operating Point ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Linear Ordinary Differential Equations ◽  
General Methodology

Transient response of gas turbine engines depends on several parameters including engine type, components’ characteristics, and operational condition. This paper briefly describes the general methodology and approach for transient sensitivity analysis of various gas turbine engines, and the results of a computer program for analysis of the transient behavior of a single spool turbojet. Based on the method of intercomponent volumes, the general methodology applicable to transient analysis of any gas turbine based system has been developed. The method results in a set of stiff, time dependent non-linear ordinary differential equations (ODE) which can be solved by an appropriate ODE solver. The coefficients of the differential equations depend on the design and operational condition of the components represented by the component maps. The initial conditions of the ODE can be any steady state operating point of the engine. A steady state engine model provides these initial conditions. The program has the capability to match the components, and obtain a steady state operating point for the engine, accept a fuel protocol and predict the transient behavior of the engine. The program has produced satisfactory results for step, ramp and sinusoidal fuel inputs, as well as ramp variation in nozzle exit area.

scholarly journals Simulation of Space Solar CBC Power Systems

1993 ◽  
Author(s):  
Zheng-Gang Diao
Keyword(s):  
Steady State ◽  
Power Systems ◽  
Power System ◽  
Computer Program ◽  
Test Data ◽  
Performance Characteristics ◽  
Brayton Cycle ◽  
Steady State Operation ◽  
Ground Test

The paper describes a computer program to simulate space solar closed Brayton cycle (CBC) power systems. The program has been written for IBM-compatible microcomputers. Either analytical equations or performance characteristics of individual components are used to model the steady-state operation of the power system. The results obtained by calculation have been compared with ground test data.

Modeling and Simulation of a Gas Turbine Engine for Power Generation

2005 ◽  
Vol 128 (2) ◽  
pp. 302-311 ◽  
Author(s):  
Qusai Z. Al-Hamdan ◽  
Munzer S. Y. Ebaid
Keyword(s):  
Power Generation ◽  
Computer Simulation ◽  
Computer Program ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Computer Simulation Program ◽  
Operating Points

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.

scholarly journals A Simple Model to Simulate Subsonic Intakes and Propelling Nozzles of Aircraft Gas Turbine Engines

1991 ◽  
Author(s):  
I. H. Ismail ◽  
F. S. Bhinder
Keyword(s):  
Simple Model ◽  
Computer Program ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Flow Properties ◽  
Area Change ◽  
Underlying Theory ◽  
Fortran 77

In this paper the subsonic intake and the propelling nozzle of aircraft gas turbine engines are modeled for the purpose of simulate. Each component is considered as a variable area duct which is divided into a number of elemental sections. Flow properties are calculated in a step by step manner in each section taking into account friction and area change. The underlying theory of the model and a brief description of the computer program are given. The program has been written in Fortran 77 and runs on IBM AT or 100% compatible micro computers.

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