OS-502 Research on a Low NO_x Combustor for a Mach 3 Supersonic Transporter Turbojet Engine(Organized Session 5: HYPR-HST/SST Propulsion System)

概要

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A methane-fueled low NO_x combustor research had been conducted under the Japanese supersonic/hypersonic propulsion research program. A unique idea of premixture jet swirl combustor (PJSC) was proposed for the ultra low NO_x combustor of a Mach 3 turbojet engine. The fuel mixing test and the fundamental combustion test were conducted for obtaining the design data and combustion characteristics in the first phase of the research. A single can type combustor was fabricated and the high temperature and high pressure combustion test was carried out for the evaluation on NO_x emission reduction capability of the PJSC concept in the second phase. In the final phase of research, a multi-sector combustor was fabricated and the performance demonstration test was conducted for a final evaluation on the pollutant exhaust emission goals and the combustor performance goals set in the HYPR project. The sequential three phased programs have completed successfully, and the project goals, such as NO_x emission, combustion efficiency, pressure loss and pattern factor of exit gas temperature at Mach 3 cruise condition, also the ICAO regulatory levels for supersonic airplane at LTO conditions, were all achieved in the performance demonstration test.
社団法人日本ガスタービン学会の論文
1999-11-14