Controllable speed casing (CSC) represents an innovative development in casing treatment technology,wherein the traditional stationary casing is reconfigured into two components:a rotatable ring and a stationary ring....Controllable speed casing (CSC) represents an innovative development in casing treatment technology,wherein the traditional stationary casing is reconfigured into two components:a rotatable ring and a stationary ring.Initial position (IP) of the rotatable ring is a cntical parameter affecting the operational effectiveness of CSC.This study investigates the influence of varying IP of the rotatable ring on the aerodynamic performance and flow stability of a high-load compressor stage,with terminal position (TP) fixed at the rotor tip trailing edge.The results reveal that positioning the rotatable ring near the rotor tip trailing edge leads to moderate improvements in stability by controlling the secondary flow at the trailing edge.However,when IP coincides with the region where the tip leakage vortex and induced vortex breakdown,CSC disrupts the upstream flow,increasing the blockage of low-energy fluid,thereby precipitating an early stall in the compressor.Conversely,positioning IP at the rotor leading edge enables CSC to effectively manage tip leakage flow,facilitating the deflection of the tip leakage vortex away from the adjacent blade pressure surface.This adjustment mitigates the blocking effect within the blade tip passage,thereby significantly enhancing the compressor's flow stability.Under these optimal conditions,CSC achieves a substantial 45.11%improvement in stable operating margin of the compressor.展开更多
Every compressor works in a limited operational range. Surge as one of the sources of this limitation has been studied for many years. In this research, an isolated blade row of compressor rotor is numerically modeled...Every compressor works in a limited operational range. Surge as one of the sources of this limitation has been studied for many years. In this research, an isolated blade row of compressor rotor is numerically modeled and solved. In order to improve operational limit and postpone the surge occurrence, a stepped blade of RAF6E with higher stall angle of attack is used to investigate the near stall flow behavior. In this study, several location of step on blades are tried and the results are compared with the case with no step on blades. It is shown that, as the step moves toward the leading edge of blades, the effect of delay on surge is reduced and even efficiency is also decreased significantly. By moving the step towards the trailing edge, surge is delayed due to the reattachment of flow after the step. Efficiency is also decreased but not in the order of the previous case.展开更多
基金the Key Project of the National Nature Science Foundation of China (Grant No.52236005)the Key Project of the Center for Basic Science of Aeroengine and Gas Turbine (Grant No.P2022-B-Ⅱ-007-001) for funding this work。
文摘Controllable speed casing (CSC) represents an innovative development in casing treatment technology,wherein the traditional stationary casing is reconfigured into two components:a rotatable ring and a stationary ring.Initial position (IP) of the rotatable ring is a cntical parameter affecting the operational effectiveness of CSC.This study investigates the influence of varying IP of the rotatable ring on the aerodynamic performance and flow stability of a high-load compressor stage,with terminal position (TP) fixed at the rotor tip trailing edge.The results reveal that positioning the rotatable ring near the rotor tip trailing edge leads to moderate improvements in stability by controlling the secondary flow at the trailing edge.However,when IP coincides with the region where the tip leakage vortex and induced vortex breakdown,CSC disrupts the upstream flow,increasing the blockage of low-energy fluid,thereby precipitating an early stall in the compressor.Conversely,positioning IP at the rotor leading edge enables CSC to effectively manage tip leakage flow,facilitating the deflection of the tip leakage vortex away from the adjacent blade pressure surface.This adjustment mitigates the blocking effect within the blade tip passage,thereby significantly enhancing the compressor's flow stability.Under these optimal conditions,CSC achieves a substantial 45.11%improvement in stable operating margin of the compressor.
文摘Every compressor works in a limited operational range. Surge as one of the sources of this limitation has been studied for many years. In this research, an isolated blade row of compressor rotor is numerically modeled and solved. In order to improve operational limit and postpone the surge occurrence, a stepped blade of RAF6E with higher stall angle of attack is used to investigate the near stall flow behavior. In this study, several location of step on blades are tried and the results are compared with the case with no step on blades. It is shown that, as the step moves toward the leading edge of blades, the effect of delay on surge is reduced and even efficiency is also decreased significantly. By moving the step towards the trailing edge, surge is delayed due to the reattachment of flow after the step. Efficiency is also decreased but not in the order of the previous case.
