高温ガス炉ガスタービン発電システム用軸流式ヘリウムガス圧縮機の端壁境界層厚さの抑制方法に関する研究(流体工学,流体機械)

概要

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Aerodynamic performance test was carried out using a 1/3 scale, 4-stage model of the helium gas compressor to investigate an effect of end-wall over-camber to prevent decrease of axial velocity in the end-wall boundary layer. The model compressor consists of a rotor, 500mm in diameter, which is driven by an electric motor at a rotational speed of 10800rpm. The rotor blade span of the first stage is 34mm. The test was carried out under the condition that the helium gas pressure of 0.88MPa, temperature of 30℃, and mass flow rate of 12.47kg/s at the inlet. A 3-dimensional aerodynamic code, which was verified using the test data, showed that axial velocity was lowered by using a blade which increased the inlet blade angle around the end-wall region of the casing side in comparison with that using the original design blade, because the inlet flow angle mismatched with the inlet blade angle of the rotor blade, as opposed to the prediction by a conventional air compressor design method. The overall adiabatic efficiency of the full scale 20-stage helium gas compressor was predicted 89.7% from the Reynolds number dependency of the test data by using the original design blade.
一般社団法人日本機械学会の論文
2009-01-25