The Hardware-in-the-Loop Simulation Study on the Control Strategy of Gas Turbine

2002 ◽  
Author(s):  
Huisheng Zhang ◽  
Ming Su ◽  
Shilie Weng
Keyword(s):  
Gas Turbine ◽  
Control Strategy ◽  
Gas Turbine Engine ◽  
Simulation System ◽  
Measuring Instruments ◽  
Hardware In The Loop ◽  
Inertia Effects ◽  
Turbine Engine ◽  
The Real ◽  
The Mathematical Model

A 3-shaft gas turbine engine for ship propulsion was taken as an object to establish the hardware-in-the-loop simulation system, which is composed of computers, real physical parts, measuring instruments, interfaces between physical parts and computers, and the network for communication, as well as the relevant software including mathematical models of the gas turbine engine. “Hardware-in-the-loop” and “volume inertia effects” are the two major features of this simulation system. In comparison with traditional methods for gas turbine simulation, the new simulation platform can implement simulation in real time and also can test the real physical parts performance through integration of the real physical parts and the mathematical model in a computer.

Hardware-in-the-Loop Simulation Study on the Fuel Control Strategy of a Gas Turbine Engine

2005 ◽  
Vol 127 (3) ◽  
pp. 693-695 ◽  
Author(s):  
Huisheng Zhang, ◽  
Ming Su, and ◽  
Shilie Weng
Keyword(s):  
Gas Turbine ◽  
Control Strategy ◽  
Gas Turbine Engine ◽  
Simulation System ◽  
Measuring Instruments ◽  
Hardware In The Loop ◽  
Inertia Effects ◽  
Turbine Engine ◽  
Acceleration Time ◽  
Surge Line

A hardware-in-the-loop simulation of a three-shaft gas turbine engine for ship propulsion was established. This system is composed of computers, actual hardware, measuring instruments, interfaces between actual hardware and computers, and a network for communication, as well as the relevant software, including mathematical models of the gas turbine engine. “Hardware-in-the-loop” and “volume inertia effects” are the two innovative features of this simulation system. In comparison to traditional methods for gas turbine simulation, the new simulation platform can be implemented in real time and also can test the physical hardware’s performance through their integration with the mathematical simulation model. A fuel control strategy for a three-shaft gas turbine engine, which can meet the requirement to the acceleration time and not exceeding surge line, was developed using this platform.

A One Dimensional, Time Dependent Inlet / Engine Numerical Simulation for Aircraft Propulsion Systems

1997 ◽  
Author(s):  
Doug Garrard ◽  
Milt Davis ◽  
Steve Wehofer ◽  
Gary Cole
Keyword(s):  
Numerical Simulation ◽  
Gas Turbine ◽  
High Frequency ◽  
Gas Turbine Engine ◽  
Simulation System ◽  
Time Dependent ◽  
Propulsion Systems ◽  
Turbine Engine ◽  
One Dimensional ◽  
Supersonic Inlet

The NASA Lewis Research Center (LeRC) and the Arnold Engineering Development Center (AEDC) have developed a closely coupled computer simulation system that provides a one dimensional, high frequency inlet / engine numerical simulation for aircraft propulsion systems. The simulation system, operating under the LeRC-developed Application Portable Parallel Library (APPL), closely coupled a supersonic inlet with a gas turbine engine. The supersonic inlet was modeled using the Large Perturbation Inlet (LAPIN) computer code, and the gas turbine engine was modeled using the Aerodynamic Turbine Engine Code (ATEC). Both LAPIN and ATEC provide a one dimensional, compressible, time dependent flow solution by solving the one dimensional Euler equations for the conservation of mass, momentum, and energy. Source terms are used to model features such as bleed flows, turbomachinery component characteristics, and inlet subsonic spillage while unstarted. High frequency events, such as compressor surge and inlet unstart, can be simulated with a high degree of fidelity. The simulation system was exercised using a supersonic inlet with sixty percent of the supersonic area contraction occurring internally, and a GE J85-13 turbojet 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.

Identification of the Mathematical Model of a Gas Turbine Engine Taking Into Account the Uncertainty of the Initial Data

2021 ◽  
Author(s):  
Oleg Baturin ◽  
Grigorii Popov ◽  
Paúl Nicolalde ◽  
Anastasia Korneeva
Keyword(s):  
Mathematical Model ◽  
Probability Distribution ◽  
Initial Data ◽  
Mathematical Models ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Bivariate Distribution ◽  
Calculation Error ◽  
Turbine Engine ◽  
The Mathematical Model

Abstract The article describes the method developed by the authors and tested on the example of the AI-25 engine. The study was focused on determining the probability distribution of the output parameters of a gas turbine engine mathematical model. The distribution was obtained considering the uncertainty of the initial data. The paper describes the identified problems and possible ways to solve them. In particular, it was found that it is not possible to study the influence of more than 7..8 input parameters on the probability distribution of output parameters with the current level of development of computer technology even using simple mathematical models. For this reason, a method has been developed to obtain reliable results while reducing the number of considered input data based on sensitivity analysis. The paper also proposed a way of comparing stochastic experimental and computational data with each other using a bivariate distribution. This method allows a precise characterisation of the calculation error using 4 numerical values. The experience obtained in the work has shown that taking into account the uncertainty of the initial data dramatically changes the process of interpreting the results. It should be noted that the obtained results are universal and can be used with other mathematical models in various industries although they were developed on the example of the mathematical model of a gas turbine engine.

scholarly journals Comparative analysis of simulation options for the real geometry of the surfaces of gas turbine engine parts

2021 ◽  
Vol 1745 (1) ◽  
pp. 012087
Author(s):  
I A Grachev ◽  
M A Bolotov ◽  
V A Pechenin ◽  
E V Kudashov ◽  
K E Kharin
Keyword(s):  
Comparative Analysis ◽  
Gas Turbine ◽  
Gas Turbine Engine ◽  
Turbine Engine ◽  
The Real ◽  
Real Geometry
Sign in / Sign up

Export Citation Format

Share Document