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Ceramic coating effect on liner metal temperatures of film-cooled annular combustor (1979)

Wear, J. D. ; Liebert, C. H. ; Claus, R. W.

In: CASI

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Publication Date: 2019-06-27

Description: An experimental and analytical investigation was conducted to determine the effect of a ceramic coating on the average metal temperatures of full annular, film cooled combustion chamber liner. The investigation was conducted at pressures from 0.50 to 0.062. At all test conditions, experimental results indicate that application of a ceramic coating will result in significantly lower wall temperatures. In a simplified heat transfer analysis, agreement between experimental and calculated liner temperatures was achieved. Simulated spalling of a small portion of the ceramic coating resulted in only small increases in liner temperature because of the thermal conduction of heat from the hotter, uncoated liner metal.

Keywords: AIRCRAFT PROPULSION AND POWER

Type: NASA-TP-1323 , E-9732

Format: application/pdf

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