研究了同心圈式旋转床转子气相干床压降(ΔPR),建立ΔPR双参数模型并通过实验对模型进行验证。实验结果表明,同心圈式旋转床ΔPR随表观气速(uG)和超重力因子(β)的增大而增大。在uG=0~6.63 m/s,β=0~562.83范围内,同心圈式旋转床转子气...研究了同心圈式旋转床转子气相干床压降(ΔPR),建立ΔPR双参数模型并通过实验对模型进行验证。实验结果表明,同心圈式旋转床ΔPR随表观气速(uG)和超重力因子(β)的增大而增大。在uG=0~6.63 m/s,β=0~562.83范围内,同心圈式旋转床转子气相干床每米压降为0.83~18.73 k Pa/m。气体相对周向速度(v(θS))随气体流量增大而增大,但转速增大v(θS)却基本不变;ΔPR双参数模型计算值和实验值的平均偏差为1.97%,正负偏差在10%以内,模型的计算值和实验值能够很好的吻合。展开更多
The paper investigates the effect of a single circumferential groove casing treatment(CGCT) on a transonic compressor rotor numerically.In particular,the effect of the groove at different axial locations on the flow f...The paper investigates the effect of a single circumferential groove casing treatment(CGCT) on a transonic compressor rotor numerically.In particular,the effect of the groove at different axial locations on the flow field is studied in detail and stall margin improvement is also discussed.The present results show that the groove close to the leading edge plays a crucial role in stabilizing the near stall flow structures and,hence,improves the stall margin.The groove at the mid-chord-section of the blade can help exchange and transfer momentums between different directions,and suppress the flow unsteadiness,leading to increased efficiency in rotor performance and extended operation range.The groove located near the blade trailing edge has limited effects on stall margin improvement and may cause additional penalty in efficiency.Through comparison with the recent work on CGCT,some common flow physics can be observed.展开更多
文摘研究了同心圈式旋转床转子气相干床压降(ΔPR),建立ΔPR双参数模型并通过实验对模型进行验证。实验结果表明,同心圈式旋转床ΔPR随表观气速(uG)和超重力因子(β)的增大而增大。在uG=0~6.63 m/s,β=0~562.83范围内,同心圈式旋转床转子气相干床每米压降为0.83~18.73 k Pa/m。气体相对周向速度(v(θS))随气体流量增大而增大,但转速增大v(θS)却基本不变;ΔPR双参数模型计算值和实验值的平均偏差为1.97%,正负偏差在10%以内,模型的计算值和实验值能够很好的吻合。
基金supported by the GE Aviation under its University Strategic Alliance(USA) programsupported by the National Natural Science Foundation of China(Grant Nos.10932005 and 11272183)
文摘The paper investigates the effect of a single circumferential groove casing treatment(CGCT) on a transonic compressor rotor numerically.In particular,the effect of the groove at different axial locations on the flow field is studied in detail and stall margin improvement is also discussed.The present results show that the groove close to the leading edge plays a crucial role in stabilizing the near stall flow structures and,hence,improves the stall margin.The groove at the mid-chord-section of the blade can help exchange and transfer momentums between different directions,and suppress the flow unsteadiness,leading to increased efficiency in rotor performance and extended operation range.The groove located near the blade trailing edge has limited effects on stall margin improvement and may cause additional penalty in efficiency.Through comparison with the recent work on CGCT,some common flow physics can be observed.
