进口畸变下缝式机匣处理改善轴流压气机性能的研究
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摘要
为了研究进口畸变下缝式机匣处理改善轴流压气机性能的机理,以亚声速单级轴流压气机的孤立转子为研究对象,在53.4%设计转速下,采用10通道非定常的数值模拟方法,开展进口畸变下轴向倾斜缝机匣处理改善轴流压气机性能的机理研究。采取在进口径向延伸段中部沿周向设置栏杆的方式产生畸变。与进口均匀实体壁机匣相比,进口畸变实体壁机匣的失速裕度改进量和峰值效率改进量分别为-5.88%和-1.44%,而进口畸变带机匣处理的失速裕度改进量和峰值效率改进量分别为24.37%和-1.09%。进口均匀实体壁机匣时,压气机的失速类型为典型的突尖型失速,即由叶顶间隙泄漏流引起的堵塞所造成。进口畸变引发叶顶处吸力面的气流分离,且气流分离沿周向呈非轴对称分布,进口畸变后叶顶通道内的低速区在很大程度上还是由叶顶间隙泄漏流所造成,只不过相比于进口均匀,叶顶处吸力面的气流分离提前发生,并且反过来又加剧叶顶间隙泄漏流的负面影响,即进口畸变后压气机失速的主要诱因没有发生本质的变化。机匣处理上、下游的喷射、抽吸过程分别对叶顶通道上游、中部的低速区气流起到激励、吹除作用,其有效地抑制了由叶顶间隙泄漏流所造成的叶顶前缘溢流和叶顶通道内压力面附近的回流,进而提高了叶顶通道的流通能力。
In order to investigate the mechanism of performance improvement for axial flow compressor with slots casing treatment under inlet distortion,the isolated rotor of test rig for subsonic single stage axial flow compressor was chosen to investigate the mechanism of performance improvement for axial flow compressor with axial skewed slots casing treatment at 53.4% design rotating speed under inlet distortion with the help of 10 passages unsteady numerical simulation method,while taking the method of setting barriers along circumferential in the middle of inlet radial extension to produce distortion. Compared to inlet uniform with solid wall,the stall margin improvement and peak efficiency improvement of inlet distortion with solid wall were-5.88% and-1.44%,while the stall margin improvement and peak efficiency improvement of inlet distortion with casing treatment became24.37% and-1.09%. As for inlet uniform with solid wall,the stall type of compressor was typical sudden stall,which resulted from the blockage caused by tip clearance leakage flow. Inlet distortion triggered flow separation at the suction surface of blade tip,and the flow separation distributed non-axisymmetrical along circumferential,the low velocity zone inside the blade tip passage was largely caused by the tip clearance leakage flow after inlet distortion,but compared to inlet uniform,the flow separation of the suction surface at the blade tip occurred in advance,and it exacerbated the negative effects of the tip clearance leakage flow in turn,i.e. the main cause of the compressor stall did not change in essence after inlet distortion. The injecting and pumping process from the upstream and downstream of casing treatment played a role in encouraging and pumping the flow of low velocity zone in the upstream and middle of blade tip passage,which restraining the leading edge spilled flow of blade tip and recirculation near the pressure surface of blade tip passage resulted by tip clearance leakage flow effectively,and improving the flow ability of blade tip passage.
In order to investigate the mechanism of performance improvement for axial flow compressor with slots casing treatment under inlet distortion,the isolated rotor of test rig for subsonic single stage axial flow compressor was chosen to investigate the mechanism of performance improvement for axial flow compressor with axial skewed slots casing treatment at 53.4% design rotating speed under inlet distortion with the help of 10 passages unsteady numerical simulation method,while taking the method of setting barriers along circumferential in the middle of inlet radial extension to produce distortion. Compared to inlet uniform with solid wall,the stall margin improvement and peak efficiency improvement of inlet distortion with solid wall were-5.88% and-1.44%,while the stall margin improvement and peak efficiency improvement of inlet distortion with casing treatment became24.37% and-1.09%. As for inlet uniform with solid wall,the stall type of compressor was typical sudden stall,which resulted from the blockage caused by tip clearance leakage flow. Inlet distortion triggered flow separation at the suction surface of blade tip,and the flow separation distributed non-axisymmetrical along circumferential,the low velocity zone inside the blade tip passage was largely caused by the tip clearance leakage flow after inlet distortion,but compared to inlet uniform,the flow separation of the suction surface at the blade tip occurred in advance,and it exacerbated the negative effects of the tip clearance leakage flow in turn,i.e. the main cause of the compressor stall did not change in essence after inlet distortion. The injecting and pumping process from the upstream and downstream of casing treatment played a role in encouraging and pumping the flow of low velocity zone in the upstream and middle of blade tip passage,which restraining the leading edge spilled flow of blade tip and recirculation near the pressure surface of blade tip passage resulted by tip clearance leakage flow effectively,and improving the flow ability of blade tip passage.
引文
[1]Society of Automotive Engineers.Inlet Total Pressure Distortion Considerations for Gas Turbine Engines[R].Aerospace Information Report 1419,1983.
[2]Luedke J G.Use of Nonlinear Volterra Theory in Predicting the Propagation of Non-Uniform Flow Through an Axial Compressor[D].Blacksburg:Virginia Polytechnic Institute and State University,2001.
[3]Wallace R M.Modal Response of a Transonic Fan Blade to Periodic Inlet Pressure Distortion[D].Blacksburg:Virginia Polytechnic Institute and State University,2003.
[4]Peters T,Burgener T,Fottner L.Effect of Rotating Inlet Distortion on a 5-Stage HP-Compressor[R].ASME2001-GT-0300.
[5]Peters T,Fottner L.Effect of Co-and Counter-Rotating Inlet Distortions on a 5-Stage HP-Compressor[R].ASME 2002-GT-30395.
[6]张环.旋转总压畸变对压气机稳定性影响的研究[D].南京:南京航空航天大学,2009.
[7]张环,胡骏,屠宝锋,等.旋转进气畸变对压气机气动稳定性及失速特性的影响[J].航空动力学报,2008,23(11):2095-2100.
[8]孙鹏.总压畸变对跨声速风扇流场结构影响的全流道数值模拟[D].哈尔滨:哈尔滨工业大学,2007.
[9]孙鹏,冯国泰.稳态周向总压畸变对小型风扇影响的全周数值模拟[J].推进技术,2006,27(3):239-242.(SUN Peng,FENG Guo-tai.Numerical Simulation of Effects of Steady Circumferential Total Pressure Distortion on a Small Fan[J].Journal of Propulsion Technology,2006,27(3):239-242.)
[10]孙鹏,冯国泰.某小型风扇内进口总压畸变引起流动损失分析[J].航空动力学报,2007,22(2):245-250.
[11]张皓光,楚武利,吴艳辉.缝式处理机匣轴向位置对压气机特性影响的机理[J].航空动力学报,2011,26(1):92-98.
[12]张皓光,楚武利,吴艳辉,等.轴向倾斜缝机匣处理影响压气机性能的机理[J].推进技术,2010,31(5):555-561.(ZHAGN Hao-guang,CHU Wu-li,WU Yan-hui,et al.Investigation of the Flow Mechanisms of Affecting Compressor Performance with Axial Skewed Slots Casing Treatment[J].Journal of Propulsion Technology,2010,31(5):555-561.)
[13]吴艳辉,张皓光,楚武利,等.双级跨音风扇轴向缝处理机匣结构优化的数值模拟研究[J].西北工业大学学报,2010,28(2):228-233.
[14]吴艳辉,张皓光,楚武利,等.双级跨声风扇双段轴向缝式机匣扩稳机理分析[J].推进技术,2010,31(2):181-186.(WU Yan-hui,ZHANG Hao-guang,CHU Wu-li,et al.Mechanism of Stall Margin Improvement of Two Stages Transonic Fan with Two-Portion Axi-al Slot Casing Treatment[J].Journal of Propulsion Technology,2010,31(2):181-186.)
[15]Walter M O,George W L,Laurence J H.Effect of Several Porous Casing Treatments on Stall Limit and on Overall Performance of an Axial-Flow Compressor Rotor[R].NASA TN D-6537,1971.
[16]Royce D M,George K,Robert J B.Effect of Casing Treatment on Overall and Blade-Element Performance of a Compressor Rotor[R].NASA TN D-6538,1971.
[17]Hall E J,Heidegger N J.Performance Prediction of End-Wall Treated Fan Rotors with Inlet Distortion[R].AIAA 96-0244.
[18]Donald S M,Matt A W.Effects of Inlet Distortion on the Stability of an Advanced Military Swept Fan Stage with Casing Treatment[R].ASME 2005-GT-68693.
[19]吴虎,高双林,黄健.等带周向槽叶尖处理机匣轴流压气机容总压畸变特性[J].推进技术,2005,26(4):324-327.(WU Hu,GAO Shuang-lin,HUANG Jian.Response of an Axial Flow Compressor Tolerant to Steady Circumferential Pressure Distortion with Casing Treatment of Circumferential Grooves[J].Journal of Propulsion Technology,2005,26(4):324-327.)
[20]黄健,吴虎,张晓东,等.周向槽机匣对轴流压气机转子畸变响应特性的影响[J].推进技术,2008,29(3):334-338.(HUANG Jian,WU Hu,ZHANG Xiao-dong,et al.Effect of Circumferential Groove Casing on the Response to Distortion of an Axial Flow Compressor Rotor[J].Journal of Propulsion Technology,2008,29(3):334-338.)
[21]熊珊,孙大坤,所秋琳,等.进气畸变条件下新型机匣处理扩稳效果实验研究[J].航空学报,2013,34(12):2692-2700.
[22]董旭,刘小华,孙大坤,等.旋转畸变条件下新型机匣处理扩稳效果试验[J].航空学报,2014,35(9):2411-2425.
[23]张皓光,王云鹏,吴俊,等.进口畸变下新型机匣处理改善压气机性能的机理研究[J].推进技术,2014,35(8):1040-1047.(ZHANG Hao-guang,WANG Yunpeng,WU Jun,et al.Investigation on Mechanism of Performance Improvement for Compressor with New Type of Casing Treatment with Inlet Distortion[J].Journal of Propulsion Technology,2014,35(8):1040-1047.)
[24]张皓光,吴俊,楚武利,等.进口畸变对轴流压气机流场影响的全通道数值研究[J].推进技术,2013,34(8):1056-1063.(ZHANG Hao-guang,WU Jun,CHU Wu-li,et al.Full-Annulus Numerical Investigation of Influence on Flow-Field in an Axial Flow Compressor with Inlet Distortion[J].Journal of Propulsion Technology,2013,34(8):1056-1063.)
[25]Huu D V,Choon S T,Edward M G.Criteria for Spike Initiated Rotating Stall[R].ASME 2005-GT-68374.
[2]Luedke J G.Use of Nonlinear Volterra Theory in Predicting the Propagation of Non-Uniform Flow Through an Axial Compressor[D].Blacksburg:Virginia Polytechnic Institute and State University,2001.
[3]Wallace R M.Modal Response of a Transonic Fan Blade to Periodic Inlet Pressure Distortion[D].Blacksburg:Virginia Polytechnic Institute and State University,2003.
[4]Peters T,Burgener T,Fottner L.Effect of Rotating Inlet Distortion on a 5-Stage HP-Compressor[R].ASME2001-GT-0300.
[5]Peters T,Fottner L.Effect of Co-and Counter-Rotating Inlet Distortions on a 5-Stage HP-Compressor[R].ASME 2002-GT-30395.
[6]张环.旋转总压畸变对压气机稳定性影响的研究[D].南京:南京航空航天大学,2009.
[7]张环,胡骏,屠宝锋,等.旋转进气畸变对压气机气动稳定性及失速特性的影响[J].航空动力学报,2008,23(11):2095-2100.
[8]孙鹏.总压畸变对跨声速风扇流场结构影响的全流道数值模拟[D].哈尔滨:哈尔滨工业大学,2007.
[9]孙鹏,冯国泰.稳态周向总压畸变对小型风扇影响的全周数值模拟[J].推进技术,2006,27(3):239-242.(SUN Peng,FENG Guo-tai.Numerical Simulation of Effects of Steady Circumferential Total Pressure Distortion on a Small Fan[J].Journal of Propulsion Technology,2006,27(3):239-242.)
[10]孙鹏,冯国泰.某小型风扇内进口总压畸变引起流动损失分析[J].航空动力学报,2007,22(2):245-250.
[11]张皓光,楚武利,吴艳辉.缝式处理机匣轴向位置对压气机特性影响的机理[J].航空动力学报,2011,26(1):92-98.
[12]张皓光,楚武利,吴艳辉,等.轴向倾斜缝机匣处理影响压气机性能的机理[J].推进技术,2010,31(5):555-561.(ZHAGN Hao-guang,CHU Wu-li,WU Yan-hui,et al.Investigation of the Flow Mechanisms of Affecting Compressor Performance with Axial Skewed Slots Casing Treatment[J].Journal of Propulsion Technology,2010,31(5):555-561.)
[13]吴艳辉,张皓光,楚武利,等.双级跨音风扇轴向缝处理机匣结构优化的数值模拟研究[J].西北工业大学学报,2010,28(2):228-233.
[14]吴艳辉,张皓光,楚武利,等.双级跨声风扇双段轴向缝式机匣扩稳机理分析[J].推进技术,2010,31(2):181-186.(WU Yan-hui,ZHANG Hao-guang,CHU Wu-li,et al.Mechanism of Stall Margin Improvement of Two Stages Transonic Fan with Two-Portion Axi-al Slot Casing Treatment[J].Journal of Propulsion Technology,2010,31(2):181-186.)
[15]Walter M O,George W L,Laurence J H.Effect of Several Porous Casing Treatments on Stall Limit and on Overall Performance of an Axial-Flow Compressor Rotor[R].NASA TN D-6537,1971.
[16]Royce D M,George K,Robert J B.Effect of Casing Treatment on Overall and Blade-Element Performance of a Compressor Rotor[R].NASA TN D-6538,1971.
[17]Hall E J,Heidegger N J.Performance Prediction of End-Wall Treated Fan Rotors with Inlet Distortion[R].AIAA 96-0244.
[18]Donald S M,Matt A W.Effects of Inlet Distortion on the Stability of an Advanced Military Swept Fan Stage with Casing Treatment[R].ASME 2005-GT-68693.
[19]吴虎,高双林,黄健.等带周向槽叶尖处理机匣轴流压气机容总压畸变特性[J].推进技术,2005,26(4):324-327.(WU Hu,GAO Shuang-lin,HUANG Jian.Response of an Axial Flow Compressor Tolerant to Steady Circumferential Pressure Distortion with Casing Treatment of Circumferential Grooves[J].Journal of Propulsion Technology,2005,26(4):324-327.)
[20]黄健,吴虎,张晓东,等.周向槽机匣对轴流压气机转子畸变响应特性的影响[J].推进技术,2008,29(3):334-338.(HUANG Jian,WU Hu,ZHANG Xiao-dong,et al.Effect of Circumferential Groove Casing on the Response to Distortion of an Axial Flow Compressor Rotor[J].Journal of Propulsion Technology,2008,29(3):334-338.)
[21]熊珊,孙大坤,所秋琳,等.进气畸变条件下新型机匣处理扩稳效果实验研究[J].航空学报,2013,34(12):2692-2700.
[22]董旭,刘小华,孙大坤,等.旋转畸变条件下新型机匣处理扩稳效果试验[J].航空学报,2014,35(9):2411-2425.
[23]张皓光,王云鹏,吴俊,等.进口畸变下新型机匣处理改善压气机性能的机理研究[J].推进技术,2014,35(8):1040-1047.(ZHANG Hao-guang,WANG Yunpeng,WU Jun,et al.Investigation on Mechanism of Performance Improvement for Compressor with New Type of Casing Treatment with Inlet Distortion[J].Journal of Propulsion Technology,2014,35(8):1040-1047.)
[24]张皓光,吴俊,楚武利,等.进口畸变对轴流压气机流场影响的全通道数值研究[J].推进技术,2013,34(8):1056-1063.(ZHANG Hao-guang,WU Jun,CHU Wu-li,et al.Full-Annulus Numerical Investigation of Influence on Flow-Field in an Axial Flow Compressor with Inlet Distortion[J].Journal of Propulsion Technology,2013,34(8):1056-1063.)
[25]Huu D V,Choon S T,Edward M G.Criteria for Spike Initiated Rotating Stall[R].ASME 2005-GT-68374.