Life Enhancement Of A Gas Turbine Engine By Temperature Control


This paper addresses the problem of enhancing the longevity of an aircraft gas turbine engine by using control strategies. Among the various component failure modes, thermal fatigue is one of major causes of damage. The approach undertaken in this paper is to reduce gas turbine inlet temperature (GTIT) of the engine. The paper considers a twin-spool turboshaft gas turbine engine to illustrate the techniques. Compressor variable geometry (CVG) setting is used as a means to meet the goal of steady state GTIT reduction. A preliminary analysis shows that it is possible to make use of CVG reset angle for reducing the steady state value of GTIT. "Linear Quadratic Gaussian with Loop Transfer Recovery" (LQG/LTR) design procedure is used to design a dynamic controller for robust stability and reducing overshoots in GTIT. © 1990, Freund Publishing House Ltd.


Electrical and Computer Engineering

Keywords and Phrases

CVG reset angle; Gas turbine engine; life-enhancement; LQG/LTR controller; Robustness; temperature-reduction

International Standard Serial Number (ISSN)

2191-0332; 0334-0082

Document Type

Article - Journal

Document Version

Final Version

File Type





© 2023 De Gruyter, All rights reserved.

Publication Date

01 Jan 1990