scholarly journals Validation of an Integrated Airframe and Turbofan Engine Simulation for Evaluation of Propulsion Control Modes

2015 ◽  
Author(s):  
Jonathan S. Litt ◽  
Yuan Liu ◽  
Thomas S. Sowers ◽  
A. Karl Owen ◽  
Ten-Huei Guo
Keyword(s):  
Turbofan Engine ◽  
Engine Simulation ◽  
Propulsion Control

Turbofan Engine Robust H-∞ Dynamical Output Feedback Control Design Based on LMI Method

2005 ◽  
Author(s):  
Xi Wang ◽  
Daoliang Tan ◽  
Tiejun Zheng
Keyword(s):  
Output Feedback ◽  
Linear Models ◽  
Nonlinear Models ◽  
Design Method ◽  
State Space Model ◽  
Output Feedback Control ◽  
Linear Matrix ◽  
Turbofan Engine ◽  
Engine Simulation ◽  
Linear State

This paper presents an approach to turbofan engine dynamical output feedback controller (DOFC) design in the framework of LMI (Linear Matrix Inequality)-based H∞ control. In combination with loop shaping and internal model principle, the linear state space model of a turbofan engine is converted into that of some augmented plant, which is used to establish the LMI formulations of the standard H∞ control problem with respect to this augmented plant. Furthermore, by solving optimal H∞ controller for the augmented plant, we indirectly obtain the H∞ DOFC of turbofan engine which successfully achieves the tracking of reference instructions and effective constraints on control inputs. This design method is applied to the H∞ DOFC design for the linear models of an advanced multivariate turbofan engine. The obtained H∞ DOFC is only in control of the steady state of this turbofan engine. Simulation results from the linear and nonlinear models of this turbofan engine show that the resulting controller has such properties as good tracking performance, strong disturbance rejection, and satisfying robustness.

Approximate Nonlinear Modeling and Feedback Linearization Control for Aeroengines

2011 ◽  
Vol 133 (11) ◽  
Author(s):  
Hui Zhao ◽  
Jinfu Liu ◽  
Daren Yu
Keyword(s):  
Feedback Linearization ◽  
Nonlinear Modeling ◽  
Loop System ◽  
Control Technique ◽  
Input Output ◽  
Close Loop System ◽  
Identification Procedure ◽  
Turbofan Engine ◽  
Engine Simulation ◽  
Feedback Linearization Control

This paper aims to develop an applicable nonlinear control technique for aeroengines. An approximate nonlinear model is presented and a rational identification procedure is given. Exact input-output feedback linearization can be easily performed on this model. The controller derived can approximately linearize the plant such that the close-loop system exhibits linear input-output dynamics locally. Modeling and controlling are exemplified and validated by a small turbofan engine. Simulation results illustrate that the modeling accuracy is good and linear close-loop system dynamics are achieved.

Real-Time Execution of a High Fidelity Aero-Thermodynamic Turbofan Engine Simulation

2012 ◽  
Vol 134 (5) ◽  
Author(s):  
Igor Fuksman ◽  
Steven Sirica
Keyword(s):  
Real Time ◽  
Thermodynamic Simulation ◽  
High Fidelity ◽  
Time Model ◽  
Turbofan Engine ◽  
Engine Simulation ◽  
Thermodynamic Simulations ◽  
Execution Speed ◽  
Asme Turbo Expo ◽  
Function Models

In the past, a typical way of executing simulations in a real-time environment had been to use transfer function models, state-variable models, or reduced-order aero-thermodynamic models. These models are typically not as accurate as the conventional full-fidelity aero-thermodynamic simulations used as a basis for the generation of real-time models. Also, there is a cost associated with the creation and maintenance of these derived real-time models. The ultimate goal is to use the high fidelity aero-thermodynamic simulation as the real-time model. However, execution of the high fidelity aero-thermodynamic simulation in a real-time environment is a challenging objective since accuracy of the simulation cannot be sacrificed to optimize execution speed, yet execution speed still has to be limited by some means to fit into real-time constraint. This paper discusses the methodology used to resolve this challenge, thereby enabling use of a contemporary turbofan engine high fidelity aero-thermodynamic simulation in real-time environments. This publication reflects the work that was initially presented at the ASME Turbo Expo 2011 (Fuksman and Sirica, 2011, “Real-Time Execution of a High Fidelity Aero-Thermodynamic Turbofan Engine Simulation,” ASME Turbo Expo, Jun. 6-10, Vancouver, Canada, Paper No. GT2011-46661).

Aero-Thermodynamic Model for Digital Simulation of Turbofan Engine

2005 ◽  
Author(s):  
R. Yadav ◽  
Yogesh Kapadi ◽  
Abhay Pashilkar
Keyword(s):  
Steady State ◽  
Thermodynamic Model ◽  
Control Volume ◽  
Digital Simulation ◽  
Operating Conditions ◽  
Turbofan Engine ◽  
Actual Performance ◽  
Engine Simulation ◽  
Modeling Software ◽  
And Control

The paper deals with the development and validation of an aero-thermodynamic model for a twin-spool mixed flow turbofan engine based on the state variable and control volume approach. Using actual performance data, the engine simulation has been performed for steady state and transient conditions with the help of MATLAB-SIMULINK. The simulation model is developed in a systematic manner. Engine states for different steady state operating conditions have been plotted. The model is fully equipped with capabilities to be integrated with the engine control design software to yield results for closed loop simulation. The results are validated against an independent and widely available modeling software called Gas turbine Simulation Program (GSP).

scholarly journals Benchmarking Gas Path Diagnostic Methods: A Public Approach

2008 ◽  
Author(s):  
Donald L. Simon ◽  
Jeff Bird ◽  
Craig Davison ◽  
Al Volponi ◽  
R. Eugene Iverson
Keyword(s):  
Power Systems ◽  
Health Management ◽  
Diagnostic Methods ◽  
Fault Detection And Isolation ◽  
Benchmark Problem ◽  
Noise Levels ◽  
Turbofan Engine ◽  
Engine Simulation ◽  
Component Faults ◽  
New Algorithms

Recent technology reviews have identified the need for objective assessments of engine health management (EHM) technology. The need is two-fold: technology developers require relevant data and problems to design and validate new algorithms and techniques while engine system integrators and operators need practical tools to direct development and then evaluate the effectiveness of proposed solutions. This paper presents a publicly available gas path diagnostic benchmark problem that has been developed by the Propulsion and Power Systems Panel of The Technical Cooperation Program (TTCP) to help address these needs. The problem is coded in Matlab™ and coupled with a non-linear turbofan engine simulation to produce “snap-shot” measurements, with relevant noise levels, as if collected from a fleet of engines over their lifetime of use. Each engine within the fleet will experience unique operating and deterioration profiles, and may encounter randomly occurring relevant gas path faults including sensor, actuator and component faults. The challenge to the EHM community is to develop gas path diagnostic algorithms to reliably perform fault detection and isolation. An example solution to the benchmark problem is provided along with associated evaluation metrics. A plan is presented to disseminate this benchmark problem to the engine health management technical community and invite technology solutions.

Non-Linear Engine Component Fault Diagnosis From a Limited Number of Measurements Using a Combinatorial Approach

2002 ◽  
Author(s):  
N. Aretakis ◽  
K. Mathioudakis ◽  
A. Stamatis
Keyword(s):  
Selection Procedure ◽  
Combinatorial Approach ◽  
Jet Engines ◽  
Turbofan Engine ◽  
Engine Simulation ◽  
Health Indices ◽  
Non Linear ◽  
Faulty Component ◽  
Component Faults

A method for diagnosing component faults of jet engines is presented. It uses non-linear gas path analysis techniques to determine the values of health parameters, with the help of a suitably formulated engine simulation model. The incentive of the method is to achieve the determination of the values of component health indices when a limited number of measured quantities is available, which do not allow the determination of all the fault indices simultaneously. A combinatorial approach is introduced, in order to circumvent the problem of the insufficient information for determining a full set of indices. After obtaining a set of possible solutions, a selection procedure is applied to isolate the ones that can give the actual fault identity. Quantification of the fault comes at a final step, when the faulty component has been identified. Different scenarios of faults on a twin spool partially mixed turbofan engine are considered in order to demonstrate the effectiveness of the method. The limitations of the method are also discussed.

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