Implanted Component Faults and Their Effects on Gas Turbine Engine Performance

[+] Author and Article Information
J. D. MacLeod

National Research Council, Ottawa, Ontario, K1A 0R6 Canada

V. Taylor

Standard Aero Ltd., Winnipeg, Manitoba, R3H 1A1 Canada

J. C. G. Laflamme

Directorate of Transport and Helicopter Engineering and Maintenance, Department of National Defence, Ottawa, Ontario, K1K 0K2 Canada

J. Eng. Gas Turbines Power 114(2), 174-179 (Apr 01, 1992) (6 pages) doi:10.1115/1.2906567 History: Received February 06, 1991; Online April 24, 2008


Under the sponsorship of the Canadian Department of National Defence, the Engine Laboratory of the National Research Council of Canada (NRCC) has established a program for the evaluation of component deterioration on gas turbine engine performance. The effect is aimed at investigating the effects of typical in-service faults on the performance characteristics of each individual engine component. The objective of the program is the development of a generalized fault library, which will be used with fault identification techniques in the field, to reduce unscheduled maintenance. To evaluate the effects of implanted faults on the performance of a single spool engine, such as an Allison T56 turboprop engine, a series of faulted parts were installed. For this paper the following faults were analyzed: (a) first-stage turbine nozzle erosion damage; (b) first-stage turbine rotor blade untwist; (c) compressor seal wear; (d) first and second-stage compressor blade tip clearance increase. This paper describes the project objectives, the experimental installation, and the results of the fault implantation on engine performance. Discussed are performance variations on both engine and component characteristics. As the performance changes were significant, a rigorous measurement uncertainty analysis is included.

Copyright © 1992 by The American Society of Mechanical Engineers
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