High-Pressure Tests of a High-g, Ultra-Compact Combustor

Abstract

The Ultra-Compact Combustor (UCC) is part of evolving technology in the development of near-constant-temperature-cycle gas turbine engines. This technology can provide a significant reduction in engine weight and size while providing large amounts of power. The UCC uses high swirl in a circumferential cavity to enhance reaction rates via high cavity gloading on the order of 3000 g’s. Increase in reaction rates translates to a reduced combustor volume. Axial flame lengths are extremely short, at about 50% those of conventional systems. High-pressure UCC tests conducted in the Air Force Research Laboratory (AFRL) High Pressure Combustor Research Facility (HPCRF) have demonstrated the feasibility of using UCC technology in advanced main combustor and Inter-Turbine Burner (ITB) systems. The UCC design integrates compressor and turbine features which will enable a shorter and less complex gas turbine engine. Experimental results from UCC testing at elevated pressure indicated that the combustion system operates at 95-99 percent efficiency over an increased operating range compared to conventional gas turbine combustion systems burning JP-8+100 fuels. This paper will describe experimental results from one UCC configuration.