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An Experimental Apparatus and Procedure for the Simulation of Thermal Stresses in Gas Turbine Combustion Chamber Panels Made of Ceramic Matrix Composites

[+] Author and Article Information
Larry Lebel

Pratt & Whitney Canada 1000, Marie-Victorin, Longueuil, Québec, Canada, J4G 1A1
Larry.Lebel@pwc.ca

Sylvain Turenne

Department of Mechanical Engineering, école Polytechnique de Montréal C.P. 6079, Succ. Centre-ville, Montréal, Québec, Canada, H3C 3A7
Sylvain.Turenne@polymtl.ca

Rachid Boukhili

Department of Mechanical Engineering, école Polytechnique de Montréal C.P. 6079, Succ. Centre-ville, Montréal, Québec, Canada, H3C 3A7
Rachid.Boukhili@polymtl.ca

1Corresponding author.

ASME doi:10.1115/1.4035906 History: Received November 01, 2016; Revised January 27, 2017

Abstract

This paper presents an experimental procedure developed to simulate the behavior of ceramic matrix composites (CMCs) under the cyclic thermal stresses of a gas turbine combustion chamber. An experimental apparatus was assembled that produces a temperature gradient across the thickness of a CMC specimen while holding the specimen at its two extremities, which simulates the bending stress that would be observed at the center of a combustor panel. Preliminary validation tests were performed in which A-N720 oxide-oxide CMC specimens were heated to a surface temperature of up to 1,160 °C using an infrared heater, which allowed for the calibration of heat losses and material thermal conductivity. The specimen test conditions were compared with predicted conditions in generic annular combustor panels made of the same material. Provided that a more powerful heat source is made available to reach sufficiently high temperatures and through-thickness temperature gradients simultaneously, the proposed experiment promises to allow laboratory observation of representative deterioration modes of a CMC inside an actual combustion chamber.

Copyright (c) 2017 by ASME
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