Advanced Control Program for Army Gas Turbine Engines

1973 ◽  
Author(s):  
A. H. White ◽  
D. F. Wills
Keyword(s):  
Control System ◽  
Control Systems ◽  
Gas Turbine ◽  
Control Program ◽  
Turbine Engines ◽  
Engine Control ◽  
Gas Turbine Engines ◽  
System Technology ◽  
Engine Control System ◽  
Advanced Control

This paper summarizes the results of a 30-month program of design, fabrication, and test of an advanced electronic engine control system for small (2 to 5-lb/sec airflow) turboshaft engines. The objective of the program was to develop engine control system technology which would be implemented in future systems to meet advanced engine requirements and to alleviate many of the problems experienced with past and present control systems.

The Electronic Control of Gas Turbine Engines

1965 ◽  
Vol 69 (655) ◽  
pp. 429-447 ◽  
Author(s):  
A. Sadler ◽  
S. Tweedy ◽  
P. J. Colburn
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Engine Fuel ◽  
Gas Turbine Engines ◽  
Turbine Engine ◽  
Engine Control System ◽  
Pumping System ◽  
Prime Movers ◽  
General Aspects

The advances made in the development of gas turbine engines during the past two decades have been remarkable. The engines have been improved tremendously in terms of power, weight, efficiency and cost. They are now being applied successfully as the prime movers for helicopters, VTOL aircraft, ground power units and for many other diverse purposes, besides the more conventional military and civil aircraft.There have been parallel advances in the development of gas turbine engine fuel systems (which for convenience may be subdivided into the “control” and the “pumping arrangement”). These systems were originally wholly hydro-mechanical in nature. Sixteen or so years ago, the first supplementary electronic devices were introduced into fuel control systems. Since then, progressively more complex hybrid electronic/hydro-mechanical systems have been employed, with a corresponding easement of the demands on the hydro-mechanical portion. In 1957 Sturrock described to this Society what is now the classic Proteus engine control system used in Britannia aircraft. The satisfactory experience gained with the Proteus system led to the adoption of a comprehensive electronic fuel control system, coupled to a relatively simple fuel pumping system, for the supersonic Olympus engine. This system has been described by Hunt and by Colburn, Tweedy and Dent in papers presented at the joint RAeS/IEE conference “The Importance of Electricity in Aircraft” in 1962. Further papers by Rush presented at the same conference and by Airey in 1963, were devoted to the more general aspects of control.

Advanced Control System Considerations for Small Shaft-Type Aircraft Gas Turbines

1970 ◽  
Author(s):  
D. A. Prue ◽  
T. L. Soule
Keyword(s):  
Control System ◽  
Gas Turbines ◽  
Evaluation Criteria ◽  
Open Loop ◽  
Engine Control ◽  
Gas Generator ◽  
Engine Control System ◽  
Power Turbine ◽  
Advanced Control ◽  
Temperature Load

The next generation of free-turbine engines in the 2 to 5-lb/sec airflow class will undergo vast improvements in performance and efficiency. The improvements will be achieved concurrent with overall reductions in size and weight. Effort is required at optimization and miniaturization of the engine control system to keep pace with these improvements. This paper describes a conceptual design of an advanced engine control system for this class of engine. It provides gas generator and power turbine control with torque, temperature, load sharing and overspeed limiting functions. The control system was concepted to accommodate, with minimum hardware changes, such variants as regenerative cycle and/or variable power turbine geometry. In addition, considerations for closed and open loop modes of control and fluidic, electronic and hydromechanical technologies were studied to best meet a defined specification and a weighted set of evaluation criteria.

Development of Small-sized Gas Turbine Engine Control System for Power Generation

2011 ◽  
Vol 14 (4) ◽  
pp. 52-56
Author(s):  
Seong-Jin Hong ◽  
Seung-Min Kim ◽  
Sim-Kyun Yook ◽  
Sam-Sik Nam
Keyword(s):  
Power Generation ◽  
Control System ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Control ◽  
Turbine Engine ◽  
Engine Control System

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 Control system of gas-turbine engines condition in operation

2016 ◽  
Vol 6 (1-2) ◽  
Author(s):  
Н. С. Кулик ◽  
А. Г. Кучер ◽  
А. В. Тарасенко
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Turbine Engines ◽  
Gas Turbine Engines
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