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 1160 °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.
An Experimental Apparatus and Procedure for the Simulation of Thermal Stresses in Gas Turbine Combustion Chamber Panels Made of Ceramic Matrix Composites
Contributed by the Combustion and Fuels Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received November 1, 2016; final manuscript received January 27, 2017; published online April 11, 2017. Editor: David Wisler.
- Views Icon Views
- Share Icon Share
- Cite Icon Cite
- Search Site
Lebel, L., Turenne, S., and Boukhili, R. (April 11, 2017). "An Experimental Apparatus and Procedure for the Simulation of Thermal Stresses in Gas Turbine Combustion Chamber Panels Made of Ceramic Matrix Composites." ASME. J. Eng. Gas Turbines Power. September 2017; 139(9): 091502. https://doi.org/10.1115/1.4035906
Download citation file:
- Ris (Zotero)
- Reference Manager