B-12 高高度滞空型無人機における軸流圧縮機翼列流れの数値解析(空力・圧縮機,一般講演)

概要

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In the jet engines of the aircrafts cruising at high altitude over 20 km with subsonic speed, the Reynolds number in terms of the compressor blade chord length becomes very low. In such an operating condition with low Reynolds number, 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. But the detail of flow mechanisms causes the total pressure loss has not been fully understood yet. In the present study, the flow fields in the transonic compressor, NASA Rotor 37, were simulated under the several conditions, which corresponded to the operations at sea level, and at a high altitude with low density and temperature. It was found that, in the case of operation at the high altitude, the separation region on the blade surface became larger, and that the radial and reverse flow around the trailing edge became stronger than those under the sea level condition.
公益社団法人日本ガスタービン学会の論文
2009-10-21