| Citation: | YI Weilin, LI Xiang. Quantitative evaluation method of three-dimensional flow loss sources in transonic compressor rotor[J]. Journal of Aerospace Power, 2026, 41（5）：20250189 doi: 10.13224/j.cnki.jasp.20250189
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The flow within a transonic compressor exhibits strong three-dimensional characteristics, with diverse and complex sources of loss. Decomposing these losses and quantitatively evaluating their contributions is of great significance. Based on analysis of transonic compressor three-dimensional flow field, the main sources of high losses in transonic compressors were identified. A loss-separation method was developed by combining vortex-identification techniques with flow-feature parameters to partition the high-loss regions. Furthermore, entropy production rate integration was employed to achieve quantitative loss evaluation. Analysis of the NASA Stage 35 compressor indicated that blade boundary layer loss, endwall loss, tip leakage vortex loss, and wake loss were major sources of flow losses in the transonic compressor rotor. Compared with the peak-efficiency condition, the proportions of boundary layer loss and wake loss decreased under near-stall conditions, while the contributions of tip leakage vortex loss and endwall loss increased significantly, reaching 21% and 20%, respectively. Although the shock wave caused by a relative tip Mach number close to 1.5 at the rotor inlet did not result in significant loss by itself, the additional flow loss caused by the interaction between the shock wave and the boundary layer required special attention.
| [1] |
HALL S R. Investigation of the effects of compressibility on profile pressure losses in axial turbine cascades [D]. Ottawa: Carleton University, 2012.
|
| [2] |
WEI Ning. Significance of loss models in aerothermodynamic simulation for axial turbines[D]. Stockholm: Royal Institute of Technology Stockholm. 2000.
|
| [3] |
王名扬, 赵胜丰, 李紫良, 等. 低雷诺数下高亚声速压气机叶型流动损失机理研究[J]. 推进技术, 2020, 41(5): 1046-1054. WANG Mingyang, ZHAO Shengfeng, LI Ziliang, et al. Flow and loss mechanism of high subsonic compressor airfoil under low Reynolds number conditions[J]. Journal of Propulsion Technology, 2020, 41(5): 1046-1054. (in Chinese
WANG Mingyang, ZHAO Shengfeng, LI Ziliang, et al. Flow and loss mechanism of high subsonic compressor airfoil under low Reynolds number conditions[J]. Journal of Propulsion Technology, 2020, 41(5): 1046-1054. (in Chinese)
|
| [4] |
刘太秋, 赵月振, 王咏梅, 等. 负荷系数0.5的高负荷单级轴流压气机设计及试验研究[J]. 航空发动机, 2022, 48(5): 1-39. LIU Taiqiu, ZHAO Yuezhen, WANG Yongmei, et al. Design and experimental investigation of a highly loaded single-stage axial compressor with loading coefficient of 0.5[J]. Aeroengine, 2022, 48(5): 1-39. (in Chinese
LIU Taiqiu, ZHAO Yuezhen, WANG Yongmei, et al. Design and experimental investigation of a highly loaded single-stage axial compressor with loading coefficient of 0.5[J]. Aeroengine, 2022, 48(5): 1-39. (in Chinese)
|
| [5] |
DICKENS T, DAY I. The design of highly loaded axial compressors[J]. Journal of Turbomachinery, 2011, 133(3): 031007. doi: 10.1115/1.4001226
|
| [6] |
DENTON J. Loss mechanisms in turbomachines[J]. Journal of Turbomachinery, 1993, 115(4): 621-656. doi: 10.1115/1.2929299
|
| [7] |
MOORE J, MOORE J G. Entropy production rates from viscous flow calculations: Part Ⅰ a turbulent boundary layer flow[R]. ASME Paper 83-GT-70, 1983.
|
| [8] |
MOORE J, MOORE J G. Entropy production rates from viscous flow calculations: Part Ⅱ flow in a rectangular elbow[R]. ASME Paper 83-GT-71, 1983.
|
| [9] |
KOCK F, HERWIG H. Entropy production calculation for turbulent shear flows and their implementation in cfd codes[J]. International Journal of Heat and Fluid Flow, 2005, 26(4): 672-680. doi: 10.1016/j.ijheatfluidflow.2005.03.005
|
| [10] |
PULLAN G, DENTON J, CURTIS E. Improving thePerformance of a turbine with low aspect ratio stators byAft-loading[J]. Journal of Turbomachinery, 2006, 128(3): 492-499. doi: 10.1115/1.2182000
|
| [11] |
ZLATINOV M B, SOOI TAN C, MONTGOMERY M, et al. Turbine hub and shroud sealing flow loss mechanisms[J]. Journal of Turbomachinery, 2012, 134(6): 061027. doi: 10.1115/1.4006294
|
| [12] |
DENTON J, PULLAN G. A numerical investigation into the sources of endwall loss in axial flow turbines[R]. ASME Paper GT2012-69173, 2012.
|
| [13] |
BORCHERDING T, BODE C, ROSENZWEIG M, et al. Entropy loss breakdown comparison for LES and RANS of a transonic compressor stage midspan section[R]. ASME Paper GT2023-102949, 2023.
|
| [14] |
GRÜBEL M, DOVIK R M, SCHATZ M, et al. A methodology for a detailed loss prediction in low pressure steam turbines[R]. ASME Paper GT2017-63404, 2017.
|
| [15] |
SAITO S, FURUKAWA M, YAMADA K, et al. Mechanisms and quantitative evaluation of flow loss generation in a multi-stage transonic axial compressor[R]. ASME Paper GT2019-90439, 2019.
|
| [16] |
ZHANG Luying, KRITIOTI L, WANG Peng, et al. A detailed loss analysis methodology for centrifugal compressors[J]. Journal of Turbomachinery, 2022, 144(5): 051013. doi: 10.1115/1.4054065
|
| [17] |
LI Hui, SU Xinrong, YUAN Xin. Entropy analysis of the flat tip leakage flow with delayed detached eddy simulation[J]. Entropy, 2019, 21(1): 21.
|
| [18] |
MAHMOOD S M H, TURNER M G, SIDDAPPAJI K. Flow characteristics of an optimized axial compressor rotor using smooth design parameters[R]. ASME Paper GT2016-57028, 2016.
|
| [19] |
WU Chengshuo, PU Kexin, LI Changqin, et al. Blade redesign based on secondary flow suppression to improve energy efficiency of a centrifugal pump[J]. Energy, 2022, 246: 123394. doi: 10.1016/j.energy.2022.123394
|
| [20] |
REID L, MOORE R D. Design and overall performance of four highly loaded, high speed inlet stages for an advanced high-pressure-ratio core compressor[M]. Washington DC: NASA, 1978.
|
| [21] |
HUNT J C R, WRAY A A, MOIN P. Eddies, streams, and convergence zones in turbulent flows[R]. Center for Turbulent Research Report CTR-S88, 1988.
|
| [22] |
LEVY Y, DEGANI D, SEGINER A. Graphical visualization of vortical flows by means of helicity[J]. AIAA Journal, 1990, 28(8): 1347-1352. doi: 10.2514/3.25224
|
| [23] |
FURUKAWA M, INOUE M, SAIKI K, et al. The role of tip leakage vortex breakdown in compressor rotor aerodynamics[J]. Journal of Turbomachinery, 1999, 121(3): 469-480. doi: 10.1115/1.2841339
|
| [24] |
CAO Zhiyuan, GAO Xi, YANG Jing, et al. Interaction mechanism between incoming vortex and tip leakage vortex breakdown of a compressor cascade[J]. Physics of Fluids, 2023, 35(9): 096102. doi: 10.1063/5.0160353
|
| [25] |
ZARIPOV D, LI Renfu, DUSHIN N. Dissipation rate estimation in the turbulent boundary layer using high-speed planar particle image velocimetry[J]. Experiments in Fluids, 2019, 60(1): 18. doi: 10.1007/s00348-018-2663-4
|
| [26] |
FERRIA H. Contribution to numerical and experimental studies of flutter in space turbines. aerodynamic analysis of subsonic or supersonic flows in response to a prescribed vibratory mode of the structure[D]. Stockholm: Royal Institute of Technology Stockholm, 2011.
|
| [27] |
COULL J D. Endwall loss in turbine cascades[J]. Journal of Turbomachinery, 2017, 139(8): 081004. doi: 10.1115/1.4035663
|
| [28] |
SCILLITOE A D, TUCKER P G, ADAMI P. Numerical investigation of three-dimensional separation in an axial flow compressor: the influence of freestream turbulence intensity and endwall boundary layer state[J]. Journal of Turbomachinery, 2017, 139(2): 021011. doi: 10.1115/1.4034797
|
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