Influence of a thermal barrier coating on the performance of a turboprop engine

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Proceedings titleASME 1992 International Gas Turbine and Aeroengine Congress and Exposition, GT 1992
ConferenceASME 1992 International Gas Turbine and Aeroengine Congress and Exposition, GT 1992, 1 June 1992 through 4 June 1992
SubjectAircraft engines; Ceramic coatings; Ceramic materials; Coatings; Engines; Marine engines; Nozzles; Surface roughness; Thermal barrier coatings; Thickness measurement; Turbine components; Uncertainty analysis; Canadian department of national defence; Coating application; Experimental installations; Measurement uncertainty analysis; National Research Council of Canada; Performance variations; Project objectives; Turbine inlet temperature; Gas turbines
AbstractUnder the sponsorship of the Canadian Department of National Defence, the Engine Laboratory of the National Research Council of Canada has evaluated the influence of applying a thermal barrier coating on the performance of a gas turbine engine. The effort is aimed at quantifying the performance effects of a particular ceramic coating on the first stage turbine vanes. The long term objective of the program is to both assess the relative change in engine performance and compare against the claimed benefits of higher possible turbine inlet temperatures, longer time in service and increased time between overhauls. The engine used for this evaluation was the Allison T56 turboprop with the first stage turbine nozzles coated with the Chromalloy RT-33 ceramic coating. The issues addressed in testing this particular type of hot section coating wares 1) effect of coating thickness on nozzle effective flow area; 2) surface roughness influence on turbine efficiency; This paper describes the project objectives, the experimental installation, and the results of the performance evaluations. Discussed are performance variations due to coating thickness and surface roughness on engine performance characteristics. As the performance changes were small, a rigorous measurement uncertainty analysis is included. The coating application process, and the affected overhaul procedures are examined. The results of the pre- and post-coating turbine testing are presented, with a discussion of the impact on engine performance. Copyright © 1992 by ASME.
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AffiliationNRC Institute for Aerospace Research; National Research Council Canada
Peer reviewedYes
NPARC number21275130
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Record identifier29ab8df4-45db-4ae8-922c-2947d3316302
Record created2015-05-11
Record modified2016-05-09
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