Integration of Control and Fuel System Components Today and Tomorrow

1969 ◽  
Author(s):  
L. J. Moulton
Keyword(s):  
Control Systems ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuel System ◽  
New Techniques ◽  
Additional Weight ◽  
Time Control ◽  
System Components ◽  
Improved Performance

New gas turbine engines, because of their requirements for improved performance at lower weights, are placing additional requirements on the control and fuel system. At the same time control and fuel system must weigh less. Integration of certain control and fuel system components is one approach which has allowed some of these seemingly conflicting requirements to be met. While future control systems may be able to achieve some additional weight savings by additional integration, further use of new techniques particularly those in electronic and pneumatic computational components seem areas to be explored if step reductions in control weight and volume are to be attained.

scholarly journals Інтелектуальний регулятор запасу газодинамічної стійкості компресора авіаційного ГТД

2021 ◽  
pp. 48-52
Author(s):  
Сергій Васильович Єнчев ◽  
Сергій Олегович Таку
Keyword(s):  
Fuzzy Logic ◽  
Nonlinear Systems ◽  
Fuzzy Control ◽  
Control Systems ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Harmonic Linearization ◽  
Gas Dynamic

The gas-dynamic stability of compressors of aircraft gas turbine engines is one of the most important conditions that determine their reliability and level of flight safety. Unstable operation of the compressor in the engine system (surge) leads to loss of thrust accompanied by an increase in gas temperature in front of the turbine and increased vibration because of large amplitudes of pressure pulsations and mass flow through the engine path. To improve the parameters of ACS aviation gas turbine engines are increasingly using regulators built using fuzzy logic algorithms. The implementation of fuzzy control algorithms differs from classical algorithms, which are based on the concept of feedback and reproduce a given functional dependence or differential equation. These functions are related to the qualitative assessment of system behavior, analysis of the current changing situation, and the selection of the most appropriate for the situation supervision of the gas turbine engine. This concept is called advanced management. ACS gas turbine engines with fuzzy regulators are nonlinear systems in which stable self-oscillations are possible. Approximate methods are used to solve the problems of analysis of periodic oscillations in nonlinear systems. Among them, the most developed in theoretical and methodological aspects is the method of harmonic linearization. The scientific problem is solved in the work – methods of synthesis of intelligent control system with the fuzzy regulator as a separate subsystem based on the method of harmonic linearization and design on its basis of fuzzy ACS reserve of gas-dynamic stability of aviation gas turbine engine. Based on the analysis of the principles of construction of fuzzy control systems, it is shown that the use of fuzzy logic provides a new approach to the design of control systems for aviation gas turbine engines in contrast to traditional control methods. It is shown that the fuzzy controller, as the only essentially nonlinear element when using numerical integration methods, can be harmonically linearized. Harmonic linearization allows using the oscillation index to assess the quality in the separate channels of fuzzy ACS aviation gas turbine engines. A fuzzy expert system has been developed for optimal adjustment of the functions of belonging of typical fuzzy regulators according to quality criteria to transients.

scholarly journals Recent Developments in Sensors for the Gas Turbine Engine

1978 ◽  
Author(s):  
P. D. Baker ◽  
R. A. Masom
Keyword(s):  
Control Systems ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Current Technology ◽  
Recent Developments ◽  
Simple Interface ◽  
Temperature And Pressure ◽  
Hostile Environments

A review of current technology applied to sensors for the measurement of speed, temperature, and pressure in gas turbine engines. The use of suitable materials and designs to overcome the hostile environments is discussed. The desirability of obtaining a simple interface with control systems is considered.

scholarly journals Application of a Thermal-Hydraulic Management Model to Gas Turbine Combustors and Fuel Systems

1999 ◽  
Author(s):  
M. A. Mawid ◽  
C. A. Arana ◽  
B. Sekar
Keyword(s):  
Gas Turbine ◽  
Air Force ◽  
Turbine Engines ◽  
Analysis Tool ◽  
Flow Control Valve ◽  
Engine Fuel ◽  
Gas Turbine Engines ◽  
Fuel System ◽  
Analysis And Design ◽  
Fuel Flow

An advanced thermal management analysis tool, named Advanced Thermal Hydraulic Energy Network Analyzer (ATHENA), has been used to simulate a fuel system for gas turbine engines. The ATHENA tool was modified to account for JP-8/dodecane fuel properties. The JP-8/dodecane fuel thermodynamic properties were obtained from the SUPERTRAP property program. A series of tests of a fuel system simulator located at the Air Force Research Laboratory (AFRL)/Wright Patterson Air Force Base were conducted to characterize the steady state and dynamic behavior of the fuel system. Temperature, pressures and fuel flows for various fuel pump speeds, pressure rise and flow control valve stem positions (orifice areas), heat loads and engine fuel flows were measured. The predicted results were compared to the measured data and found to be in excellent agreement. This demonstrates the capability of the ATHENA tool to reproduce the experimental data and, consequently, its validity as an analysis tool that can be used to carry out analysis and design of fuel systems for advanced gas turbine engines. However, some key components in the fuel system simulator such as control components, which regulate the engine fuel flow based on predetermined parameters such as fan speed, compressor inlet and exit pressures and temperatures, combustor pressure, turbine temperature and power demand, were not simulated in the present investigation due to their complex interactions with other components functions. Efforts are currently underway to simulate the operation of the fuel system components with control as the engine fuel flow and power demands are varied.

Fuel Systems for Gas Turbine Engines

1955 ◽  
Vol 59 (539) ◽  
pp. 727-737 ◽  
Author(s):  
O. N. Lawrence
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Fuel System ◽  
Fuel Flow ◽  
Design Office ◽  
System Engineer ◽  
Made In

Seven years ago a paper on this same subject was read before the Main Society. This has been used as a basis from which to start.It will be seen that great strides have been made in performance, and the projects in the Design Office and on the drawing boards particularly, would even satisfy parliamentary critics. In Derby, however, where jet lift was conceived, such things are well known. From the fuel system standpoint in general the changes in requirements have been routine, merely much greater fuel demands, greater altitudes and air speeds and hence, a greater range of fuel flow, and it is this which gives the fuel system engineer his greatest worries. Beyond this there is always the need for smaller and lighter units in fancy shapes.

Pneumatic Starting Systems

1967 ◽  
Author(s):  
Robert J. Von Flue
Keyword(s):  
Gas Turbine ◽  
Energy Utilization ◽  
Turbine Engines ◽  
General Description ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Air Turbine ◽  
System Components ◽  
Optimum Arrangement ◽  
Gas Turbine Compressor

Pneumatic starting systems for gas turbine engines are discussed. A general description of various energy sources, system components and arrangements is included. Systems are reviewed from the standpoint of energy utilization, versatility and reliability. It is concluded that the auxiliary gas turbine compressor/air turbine starter combination is the optimum arrangement, and, without a doubt, it will continue to be the primary starting means in gas turbine engine applications.

Low-leakage and High-Flow Regenerators for Gas Turbine Engines

1993 ◽  
Vol 207 (3) ◽  
pp. 195-202 ◽  
Author(s):  
D G Wilson
Keyword(s):  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines ◽  
Regenerative Heat ◽  
Wear Rates ◽  
Low Leakage ◽  
The Matrix ◽  
Potential Applications ◽  
Improved Performance ◽  
Burning Coal

The preliminary analysis and development of two new forms of regenerative heat exchanger that seem to promise greatly improved performance characteristics is described. To reduce drastically the usually high leakage and high seal wear rates suffered by present rotary regenerators, discontinuous rotation of the matrix has been studied, with seals that clamp the matrix during the stationary periods. To enable the regenerative gas turbine cycle to be used at high powers, regenerators consisting of movable ceramic modules are being investigated. The potential applications of the discontinuous-rotation type are particularly to small lightweight gas turbine engines such as those for automotive applications and to helicopters and light turboprop aircraft. The modular regenerator is being studied in application to burning coal and biomass of gas turbine engines and to larger marine and stationary base-power engines with power outputs of up to (and possibly beyond) 100 MW.

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