scholarly journals Error Evaluation of Hardware-in-the-Loop Simulation of a Gas Turbine Engine Fuel Controller

2018 ◽  
Vol 41 (4) ◽  
pp. 47-60
Author(s):  
Morteza Montazeri-Gh ◽  
Soroush Abyaneh
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Fuel ◽  
Hardware In The Loop ◽  
Error Evaluation ◽  
Turbine Engine

Effect of Nonlinear Characteristic of the Gas Turbine Engine Fuel System With Hardware-in-the-Loop

2018 ◽  
Author(s):  
Jinwei Chen ◽  
Jingxuan Li ◽  
Shengnan Sun ◽  
Huisheng Zhang
Keyword(s):  
Gas Turbine ◽  
Dead Zone ◽  
Gas Turbine Engine ◽  
Supply System ◽  
Hardware In The Loop ◽  
Nonlinear Characteristics ◽  
Turbine Engine ◽  
Zone Width ◽  
Servo Actuator ◽  
Hydraulic Servo

Fuel supply system, the regulation system for fuel delivery to the combustor, is one of the most important auxiliary systems in a gas turbine engine. Commonly, the fuel supply system was always simplified as a linear system. In fact, gas turbine engines almost use a hydromechanical main fuel control system which consists of electro-hydraulic servo actuator and fuel metering unit. These components have several nonlinear characteristics such as hysteresis, dead zone, relay, and saturator. These nonlinear characteristics can directly affect the performance a gas turbine engine. In this paper, a three-shaft gas turbine engine was taken as a research object. Firstly, a mechanism model of the fuel control system considering the nonlinear links was developed based on the hydro-mechanical theory. Then, the effect of dead zone-relay characteristic of the servo amplifier in electro-hydraulic servo actuator was analyzed. The results show that the dead zone width has great effect on the dynamic performance of the gas turbine engine. The fuel flow rate will be oscillating with small dead zone width. The parameters of the gas turbine engine will be stable with the increase of dead zone width. However, the larger dead zone width causes the hysteresis and the increase of the dynamic response time. At the same time, an improvement method with a two-dimensional fuzzy compensation was proposed. The results show that the fuzzy compensation can effectively solve the oscillation problem caused by the dead zone-delay. Finally, a Hardware-In-the-Loop (HIL) system is developed which is based on an electro-hydraulic servo actuator facility and a real-time software component of the gas turbine engine. An experiment is conducted on the HIL test rig to validate simulation result. The results show that the experiment matches well with the simulation results.

Fuzzy-Based Gas Turbine Engine Fuel Controller Design Using Particle Swarm Optimization

2011 ◽  
Vol 110-116 ◽  
pp. 3215-3222 ◽  
Author(s):  
M. Montazeri-Gh ◽  
E. Mohammadi ◽  
S. Jafari
Keyword(s):  
Particle Swarm Optimization ◽  
Gas Turbine ◽  
Fuzzy Logic Controller ◽  
Particle Swarm ◽  
Gas Turbine Engine ◽  
Time Response ◽  
Rule Base ◽  
Engine Fuel ◽  
Swarm Optimization ◽  
Turbine Engine

This paper presents the application of Particle Swarm Optimization (PSO) algorithm for optimization of the Gas Turbine Engine (GTE) fuel control system. In this study, the Wiener model for GTE as a block structure model is firstly developed. This representation is an appropriate model for controller tuning. Subsequently, based on the nonlinear GTE nature, a Fuzzy Logic Controller (FLC) with an initial rule base is designed for the engine fuel system. Then, the initial FLC is tuned by PSO with emphasis on the engine safety and time response. In this study, the optimization process is performed in two stages during which the Data Base (DB) and the Rule Base (RB) of the initial FLC are tuned sequentially. The results obtained from the simulation show the ability of the approach to achieve an acceptable time response and to attain a safe operation by limiting the turbine rotor acceleration.

Comparison of measurements and predictions of flow in a gas turbine engine fuel nozzle

2000 ◽  
Author(s):  
A. Brankovic ◽  
L. Porter ◽  
R. McKinney ◽  
H. Ouyang ◽  
J. Kennedy ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Fuel ◽  
Turbine Engine ◽  
Fuel Nozzle

Impact of Negative Factors on Performance of Cryogenic Unit of LNG Gas-Turbine Engine Fuel System

2020 ◽  
Vol 56 (5-6) ◽  
pp. 351-359
Author(s):  
I. A. Arkharov ◽  
E. S. Navasardyan ◽  
A. S. Krotov ◽  
Ya. V. Samokhvalov
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Fuel ◽  
Fuel System ◽  
Turbine Engine ◽  
Negative Factors

Modification of the Rolls-Royce Model MT5S Gas Turbine Engine Fuel Nozzle for Extended Fuel Flow Rates

2014 ◽  
Author(s):  
Jack Halsey ◽  
Leonard Overton ◽  
Philip Buelow ◽  
David Bretz
Keyword(s):  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Engine Fuel ◽  
Flow Rates ◽  
Turbine Engine ◽  
Operating Range ◽  
Fuel Flow ◽  
Fuel Nozzle

The Rolls-Royce Model MT5S gas turbine engine was selected for use in the auxiliary turbine genset (ATG) of the DDG1000. This engine initially used the same fuel nozzle as the Model 501-K34 engine used in the DDG51 class ships. The Model MT5S can operate at higher powers levels and fuel flows. The fuel nozzle for the Model MT5S gas turbine engine experienced coking problems at the higher fuel flows. This paper discusses the investigation and solution to the problem to extend the operating range of the fuel nozzle for other applications.

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.

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