Design and Analysis of a Compact Combustor for Integration with a JetCat P90 RXi
Technical Report,01 Sep 2018,01 Mar 2020
AIR FORCE INSTITUTE OF TECHNOLOGY WRIGHT-PATTERSON AFB OH WRIGHT-PATTERSON AFB United States
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Ultra Compact Combustors are a novel approach to modern gas turbine combustor designs that look to reduce the overall combustor length and weight. A previous study integrated an Ultra Compact Combustor into a JetCat P90 RXiturbine engine and achieved self-sustained operation with a length savings of 33 relative to the stock combustor. However, that combustor could not operate across the full stock engine performance range due to flameout at increasedmass flow rates as reactions were pushed out of the primary zone. To ensure reactions stayed in the primary zone, a new design with a larger combustor volume was conceived maintaining the same axial dimensions. The design wasinvestigated computationally for generalized flow patterns, pressure losses, exit temperature profiles, and reaction distributions throughout the combustor at three engine power conditions. The combustor was then built and tested inthe JetCat P90 RXi with and without rotating turbomachinery. The combustor responded well to changes in air and fuel flow rates and operated with rotating hardware.