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Development of Engine Control Unit for Gas Turbine Starter of Fighter Aircraft

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Development of Engine Control Unit for Gas Turbine Starter of Fighter Aircraft International Journal of Science and Research (IJSR) ISSN: 2319-7064 ResearchGate Impact Factor (2018): 0.28 | SJIF (2019): 7.583 Development of Engine Control Unit for Gas Turbine Starter of Fighter Aircraft Rupini Ram V K1, Dr. Basavaraju C2 1P.G. Student, Department of Electronics and Communication Engineering, Cambridge Institute of Technology, Bangalore, India 2Professor, Department of Electronics and Communication Engineering, Cambridge Institute of Technology, Bangalore, India Abstract: The progress in the gas turbine field and advanced measuring techniques have been dramatically accelerated with the advent of modern control during the last two decades. In this scenario, this project is aimed at study and design of an Engine Control Unit (ECU) for a Turbo Shaft Gas Turbine Starter. The starter is used to start the main engine of a fighter aircraft. The ECU is a dual lane controller which controls the fuel flow to the Gas Turbine Starter engine to maintain its speed, temperatures and pressures in safe limits for proper starting of the main aero engine. It is a Microcontroller based Digital Electronic Control. It changes a 3-phase stepper motor position either in forward (clockwise) or backward (anticlockwise) direction which in turn modulates the fuel to the combustion chamber of the starter engine to maintain its structural parameters (rotor speed) and thermodynamic parameters (pressures and temperatures) within the specified limits for safe operation. Keywords: Engine Control Unit, Gas Turbine Starter, Fighter Aircraft, Stepper Motor 1. Introduction processor is detected, the Emergency processor takes the control of the stepper motor and the outputs. There are several ways of starting the main engine of a fighter aircraft. One of the method is starting through 2. Literature Survey another small gas turbine engine (Gas Turbine Starter) or simple starter. B. S. Bhangu and Kaushik Rajashekara, in their paper, “Control strategy for electric starter generators embedded in The starter engine is also a Gas turbine engine whose gas turbine engine for aerospace applications”, explain that structural parameters such as speed and thermodynamic due to space constraints a practical solution for UAVs is to parameters such as Temperature and pressure are to be employ electricstarter generators (ESG) embedded in gas contained within a specified limit to avoid any catastrophic turbine engines to facilitate electric engine crank, aid the failure. This is accomplished by properly controlling the engine to the desired idle speed and generate power to drive admission of fuel into the starter engine. the onboard auxiliaries. However, the traditional sensors that provide accurate knowledge of the machine rotor position to Engine Control Unit (ECU) is an Avionics unit which plays ease precise control of the ESG cannot be used because of an important role in control of fuel flow to the Starter Unit, the adverse operating conditions. The entire hardware and which starts the main engine. It provides full authority control architecture was tested on an experimental test rig control of fuel flow to the Starter Unit. The ECU takes input using a dynamometer to mimic the gas turbine engine. from various engine mounted sensors and takes appropriate Following the testing, the system was commissioned into the decision to control the fuel flow into the starter engine. gas turbine Small Electric Engine Demonstrator (SEED). Apart from Engine Control, the ECU also needs to Song Ma, Jianguo Tan, Yongqian Ning and Zichang Gao, handshake with appropriate aircraft avionics Line presented a paper on “Modeling and simulation of gas Replaceable Units (LRU) for indication to the outside World turbine starter and fuel control system”, which explains that and also to the pilot. Engine Control Unit has to ensure Gas turbine starter is an important component of aero-engine Smooth light up scheduling, Surge free acceleration, gas turbine starting system, and its performance directly Governing at maximum speed until output shaft speed affects the starting ability of an aero-engine. In order to meet reaches self-sustaining speed, Shut off the engine after the necessities of starter power for different types of large reaching cut-off speed, or timeout, or over temperature and engines and provide theoretical foundation for modification speed runaway conditions. of starters, the paper focuses on the performance of gas turbine starter and its fuel control system. The design and ECU is a microcontroller based Digital PID controller to operating principle of the system were firstly analysed. start the Starter Unit, accelerate and control the Starter Unit Based on the AMESim mechanical hydraulic simulation by controlling the fuel flow with the help of stepper motor software, the component-level model of fuel control system which in turn starts the Main Engine. It has two identical was built. Then the model of the starter portion was PCBs, Main Processor card (Lane 1) and the Emergency established according to the fundamental principles of gas Processor card (Lane 2). During the normal functionality, dynamics and thermodynamics. By comparing the the main processor will be controlling the stepper motor and simulation results of the model with the experimental data, the outputs. The Emergency processor will be checking the results showed that the established model met the health of the main processor. Once any failure in the main requirements of engineering and thus, provided a simulation platform for future research of gas turbine starter. Volume 9 Issue 8, August 2020 www.ijsr.net Licensed Under Creative Commons Attribution CC BY Paper ID: SR20811210304 DOI: 10.21275/SR20811210304 732 International Journal of Science and Research (IJSR) ISSN: 2319-7064 ResearchGate Impact Factor (2018): 0.28 | SJIF (2019): 7.583 amperes at engine speeds from 4,000–8,000 rpm. The Weili Dai, TongcaiXiu, Huizhen Wang and Yangguang electric system designed to control the starter-generator and Yan, explain in their paper, “Control of a novel dual stator its supporting components were patterned, in the early doubly salient aircraft engine starter-generator”, that a novel designs, after comparable systems used on standard dual stator doubly salient Aircraft Engine Starter-Generator reciprocating-type airplanes. Modifications, and in some System has been designed and constructed for an aircraft respects complete redesign, of parts of the control system engine application. The system is based on a dual-stator were essential in order to provide a system which would doubly salient Electromagnetic machine, which was chosen perform according to the more exacting requirements for its simplicity, ruggedness, high speed capability, low demanded of it. torque ripple in motoring and low output voltage ripple in generating. The paper describes the motor control system S.R. MacMinn and J.W. Sember, in their paper, “Control of algorithms and hardware which were used to control the a switched-reluctance aircraft engine starter-generator over a motor over its operating speed range from standstill to very wide speed range”, explain that an electric direct-drive 11425rpm in both motoring and generating modes. There are gearless starter-generator had been designed and built for an novel features in this starter-generator control system, the aircraft-engine application. The system was based on particular motor structure, angle advanced control strategy switched reluctance motor, which was chosen for its which were adopted in aircraft engine starting process, simplicity, ruggedness, high-speed capability, and which controlled the value of advanced angle to maintain efficiency. The motor control system algorithms and optimum torque at medium and high speed automatically. hardware were used to control the motor over its operating The transition between starting and generating process was speed range from standstill to 48000 RPM in both satisfied by a hardware-based digital commutation controller monitoring and generating modes. The unique features of which generated phase firing pulses for the inverter based on the starter-generator control system are a closed-loop the machine rotor angle, pulse width, and pulse advance. regulator which controls the amount of firing angle advance The results of aircraft engine cold start show that the to sustain optimum at high speed, and a hardware based brushless starter-generator system had good starting digital commutation controller which generates phase firing character and smooth starting torque. pulses for the inverter, pulse width, and pulse advance. R. Bojoi, A. Cavagnino, A. Tenconi and S. Vaschetto, “Control of Shaft-Line-Embedded Multiphase 3. Hardware Implementation Starter/Generator for Aero-Engine”, discuss thattheir paper deals with a shaft-line-embedded multiphase electrical Engine Control Unit machine to be connected to the high-pressure shaft of an ECU is microcontroller-based unit which computes the open-rotor jet engine. An asymmetrical six-phase induction control function to regulate the fuel flow and to provide machine (IM) was proposed for this application. The main proper dynamic characteristics and steady state speed focus of the paper was on the control of the six-phase IM, to holding characteristics. The ECU and GTS interface is as verify its overload capabilities and postfault operations. The shown below: realized control used a direct-flux vector control scheme- based on a double-stator approach, where each 3-phase winding set was independently controlled.
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