【摘要】 由德国宝马·罗·罗 (BRR)、中国燃气涡轮研究院 (GTE)和德国宇航院 (DLR)联合开展了“叶背表面曲率的变化对高压涡轮尾迹损失的研究”。此课题包括三套涡轮叶栅 ,G1由BRR气动设计 ,DLR和GTE共同试验 ;G2 由BRR气动设计 ,GTE试验 ;G3 叶栅由GTE气动设计、加工和试验。通过研究得出了G1、G2 和G3 三套叶栅 ,在 β1=41.4°、5 6 .4°和 2 6 .4°,M2tis =0 .70、0 .85、1.0和 1.15时 ,叶背表面带和不带附面层转捩线的试验结果。更多还原

【Abstract】 A Subject "Impact of Suction Surface Shape on High Pressure Turbine Trailing Edge Loss" has been conducted by BRR, GTE and DLR.It includes three sets of turbine plane cascades (G 1?G 2 and G 3) .G 1 is designed by BRR and tested by DLR and GTE. G 2 is designed by BRR and tested by GTE.G 3 is designed, manufactured and tested by GTE. Test results of G 1?G 2 and G 3 cascades at β 1=41.4°56.4°and 26.4°,M 2tis =0.7, 0.85, 1.0 and 1.15 with and without trip wire are given in the report.更多还原