A-14 高高度無人機における圧縮機翼列の空力特性に関する研究(空力III,一般講演)

概要

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In the jet engines on the aircrafts cruising at high altitude over 20 km with subsonic speed, the Reynolds number in terms of the compressor blades becomes very low. In such operating conditions, it is widely reported that total pressure loss of the air flow through the compressor cascades increases dramatically due to separation of the boundary layer and the secondary-flow. In the present study, the flow fields in the transonic compressor were simulated under the several conditions, which corresponded to the operation at sea level static and at high altitude with low density and temperature. It was found that the compressor performances deteriorated at high altitude conditions. In the flow fields of the compressor cascade, the separation region on the blade surface became lager, and the radial and reverse flow around the trailing edge became stronger than those under sea level static condition.
公益社団法人日本ガスタービン学会の論文
2008-10-01