The research and development of a turbo jet combustor for a Mach 3 class supersonic transport is underway, as well as the other components of the HST programme in JAPAN. This research and development aims finally at achieving a combustor exit temperature of 1973K while maintaining low NOx levels, high durability, and good exit temperature distribution.

This paper describes the interim status of the combustor research and development, in particular, the liner cooling system and exit temperature distribution control technique.

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