Design of a Gas Turbine Based Air Start Unit for Larger Aircraft Engine

2004 ◽  
Author(s):  
Li-Chieh Hsu ◽  
Wu-Chi Ho ◽  
Chien-Ching Hsueh
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Flow Rate ◽  
Centrifugal Compressor ◽  
Aircraft Engine ◽  
Aircraft Engines ◽  
Air Flow Rate ◽  
Turbine Engine ◽  
Engine Control System ◽  
Compact Design

A novel Air Start Unit powered by gas turbine engine is developed. The feature of this unit is that it can start various aircraft engines, including the hundred thousand pound thrust class engine like GE90, with different air flow rate in a compact design. This paper introduces the complete design and development of large centrifugal compressor, digital engine control system, testing of gas turbine system.

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

Experimental Analysis of Combustion in Gas Turbine

2019 ◽  
Author(s):  
M. S. N. Murthy ◽  
Subhash Kumar ◽  
Sheshadri Sreedhara
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Experimental Analysis ◽  
Air Flow ◽  
Measuring System ◽  
Maximum Pressure ◽  
Gear Pump ◽  
Air Flow Rate ◽  
Gas Turbine Combustor ◽  
Turbine Engine

Abstract This paper presents the methodology and results of an experimental analysis of combustion in a gas turbine combustor. The experimental setup is designed to imitate the conditions of a working gas turbine engine (GT), using an actual gas turbine combustor. Air is supplied by a heavy-duty air compressor at a maximum pressure of 7 bar to the combustor through an air pipe catering to the developing length. The air flow rate is measured using an ASME standard Venturimeter along with a manometer. The air flow rate and pressure are controlled by a combination of air outlet valve placed before developing length and by a throttle orifice in the exhaust duct at combustor outlet. Diesel fuel used in the experiments is provided at required atomizing pressure by a gear pump. Mass flow rate and pressure of fuel is controlled by combination of valves and varying the speed of gear pump using a variable speed electric motor. Combustion is initiated in a conventional pilot ignition unit using a spark plug and fuel burner. Fuel flow rate is measured accurately using a unique catch and time measuring system at the inlet of the gear pump.

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.

scholarly journals Aerodynamic improvement of an aircraft gas-turbine engine fan

2021 ◽  
Vol 2021 (3) ◽  
pp. 23-29
Author(s):  
Yu.A. Kvasha ◽  
◽  
N.A. Zinevych ◽  
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Turbine Engines ◽  
Gas Flows ◽  
Gas Turbine Engines ◽  
Air Flow Rate ◽  
Profile Angle ◽  
Turbine Engine ◽  
Blade Height ◽  
Second Stage

This work is concerned with the development of approaches to the aerodynamic improvement of axial-flow compressors for gas-turbine engines. The aim of this work is the aerodynamic improvement of an aircraft gas-turbine engine two-stage fan by numerical simulation of 3D turbulent gas flows. The approach used in this study features: varying the spatial shape of the fan blades for the first- and the second-stage impeller by varying the profile angle along the blade height; formulating quality criteria as the mean integral values of the power characteristics of each impeller of the fan over the operating range of the air flow rate through the impeller; and searching for advisable values of the impeller blade parameters by scanning the independent variable range at points that form a uniformly distributed sequence of small length. The basic tool is a numerical method developed at the Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine, which simulates 3D turbulent gas flows using the complete averaged Navier¬–Stokes equations and a two-parameter turbulence model. It is shown that varying the profile angle along the blade height for the fan second-stage impeller allows one to increase the air compression ratio in the fan by about 2 percent throughout the operating range of the fan air flow rate without affecting the adiabatic efficiency of the fan. On the whole, by the example of the fan under study, the paper considers the assumption that the aerodynamic improvement of compressors at the initial stage can be made on an impeller by impeller basis. It is shown that in further analysis providing the gas-dynamic stability of the compressor should be accounted for. The results obtained are intended to be used in the aerodynamic improvement of multistage compressors for aircraft gas-turbine engines and various power plant.

Full Authority Digital Engine Controller for Marine Gas Turbine Engine

2006 ◽  
Author(s):  
B. Githanjali ◽  
P. Shobha ◽  
K. S. Ramprasad ◽  
K. Venkataraju
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Fuel ◽  
Electronic Control ◽  
Gas Generator ◽  
Turbine Engine ◽  
Engine Control System ◽  
Control Units ◽  
Commercial Off The Shelf

A full authority digital engine control system (FADEC) has been configured for the marine gas turbine engine being developed at the Gas Turbine Research Establishment, Bangalore, India. This paper presents the development of a prototype FADEC for this aero-derivative marine gas turbine engine. A dual-redundant architecture, with two identical digital electronic control units (DECU) in an active-standby configuration, was chosen to provide the necessary reliability, availability and maintainability. The system provides automatic control of engine fuel flow and compressor variable geometry, without exceeding parameter limits, so as to control either the speed of the gas generator or the power turbine in order to meet the power demanded. While the control units incorporate hardware and software features to detect and accommodate faults, an independent electronic trip system was included as a part of the overall control system to handle those situations resulting in uncontrolled overspeeding or safety interlock requirements. Recognizing the global trend towards the use of commercial off the shelf (COTS) technology, the system was configured with industry proven hardware and software. In addition, a hydro-mechanical backup control provides limited operational capability in the event of electronic control failure.

scholarly journals Gas-Turbine Engine Control System of the Unmanned Airplane

2004 ◽  
Vol 37 (6) ◽  
pp. 1049-1053
Author(s):  
A.S. Kulik ◽  
V.F. Symonov ◽  
S.N. Pasichnik ◽  
A.V. Komkov
Keyword(s):  
Control System ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Control ◽  
Turbine Engine ◽  
Engine Control System

scholarly journals AUTOMATION CONTROL SYSTEM OF TECHNICAL CONDITION OF GAS TURBINE ENGINE COMPRESSOR

2019 ◽  
pp. 121-128
Author(s):  
Микола Сергійович Кулик ◽  
Володимир Вікторович Козлов ◽  
Лариса Георгіївна Волянська
Keyword(s):  
Gas Turbine ◽  
Flow Rate ◽  
Static Pressure ◽  
Air Flow ◽  
Gas Turbine Engine ◽  
Technical Condition ◽  
Operating Conditions ◽  
Air Flow Rate ◽  
Turbine Engine ◽  
Flow Duct

The article is devoted to one of the approaches to the construction of an automated system for solving the problems of diagnostics and monitoring of the flow duct of aircraft gas turbine engines and gas turbine plants. Timely detection of faults and subsequent monitoring of their development in operation are possible thanks to automated systems for assessing the technical condition of engines. This is particularly relevant in operating conditions as the knowledge of the technical condition of the engine is necessary in any engine maintenance system allows  to choose the content and timing of maintenance, repair of the flow duct of gas turbine engines and gas turbine plants, as well as commissioning. The engineering technique, which can be applied at performance of maintenance and at stages of tests and debugging of aircraft engines, is considered. The automated system implements a method of measuring the air flow through the compressor and a technique for assessing the technical condition of the compressor by the relative change in air flow. To determine the air flow rate through the gas turbine engine, it is sufficient to measure only static pressure values in the flow part. The static pressure receivers are not located in the flow part and do not obscure it, and thus do not affect the compressor gas dynamic stability margin. The inspection area is selected for measuring in the flow duct of the air intake. Static pressure in the maximum and minimum cross sections of the chosen area is measured; the maximum cross-section area of the flow duct, the total temperature of the air flow is measured outside the air intake.  To determine the air flow rate, the functional dependence of the air flow rate on the static pressure is used. The algorithm for monitoring and diagnosing the operating condition of the engine is based on a comparison of the actual values of air flow rate with the air flow rate determined during the control tests or when using a mathematical model adapted for this gas turbine engine. The positive effect of the using of the proposed automated control system of technical condition is that the air flow rate measured under operating conditions will significantly increase the objectivity of the control of the operation and technical condition of the gas turbine engine.

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