| Citation: | MA Chaofan, SUI Xiuming, PU Jian, et al. The impact of end-wall fillet on secondary flow losses in a highly-loaded rotor with low aspect ratio and larger camber angle[J]. Journal of Aerospace Power, 2026, 41（2）：20230652 doi: 10.13224/j.cnki.jasp.20230652
|
The interference mechanisms between the rotor passage vortex and tip leakage vortex were analyzed numerically to control the secondary flow losses in a highly loaded rotor with a low aspect ratio and large camber angle. The impact of end-wall fillets on these losses was also investigated. The results revealed that, at the leading edge up to 50% axial chord length, after the horseshoe vortex was evolved and formed into the hub passage vortex, it quickly moved to the upper part of the blade, limiting the development of the shroud passage vortex and reducing the vorticity of the tip leakage vortex. After 50% axial chord length, the high-speed shear effects between the leakage flow and the mainstream were intensified, rapidly strengthening the tip leakage vortex. The shroud passage vortex was pushed away from the suction surface by the combined action of the hub passage vortex and tip leakage vortex, which prevented it from sucking low-energy fluid onto the suction surface and restricted its growth. Due to the entrainment effect of the passage vortex system, low-energy fluid was accumulated at the blade tip, increasing the flow losses and deviation angles there. As a result, the main cause of losses was attributed to the secondary flow caused by the end-wall. The effect of end-wall fillet on the highly loaded rotor with a low aspect ratio and large camber angle was significantly different from the traditional turbines. When the fillet radius was smaller than the boundary layer thickness at the leading edge of the hub, the fillet could weaken the strength of the horseshoe vortex and the hub passage vortex, but it could increase their influential region. This intensified the entrainment effect of the vortex system, reduced the accumulation of low-energy fluid within the 30%—50% axial chord length range on the suction surface, and increased the radial pressure gradient. Therefore, as the radial migration of the hub passage vortex decreased, its entrainment of low-energy fluid on the suction surface was reduced, resulting in reduced vorticity. When the fillet radius was larger than the boundary layer thickness at the leading edge of the hub, the fillet could weaken the effect region of the horseshoe vortex and the hub passage vortex, increasing the accumulation of low-energy fluid on the suction surface close to the blade root and decreasing the radial pressure gradient. Then the radial migration position and vorticity of the hub passage vortex increased, and low-energy fluid was accumulated on the suction surface. Consequently, turbine efficiency decreased as the fillet radius increased.
| [1] |
MINATO R, NAKATA D, UCHIUMI M, et al. Overspeeding characteristics of turbomachinery for gas generator cycle air turbo ramjet engine[J]. Propulsion and Power Research, 2022, 11(4): 444-456. doi: 10.1016/j.jppr.2022.10.001
|
| [2] |
FERNANDEZ V. Simulation, design and analysis of air-breathing combined-cycle engines for high speed propulsion[D]. Madrid, Spain: University of Technology of Madrid, 2013.
|
| [3] |
刘洋, 李江, 刘诗昌, 等. 固体燃料空气涡轮火箭发动机方案和技术研究[J]. 推进技术, 2017, 38(2): 249-256. LIU Yang, LI Jiang, LIU Shichang, et al. Scheme and technology investigation on solid propellant air turbo rocket[J]. Journal of Propulsion Technology, 2017, 38(2): 249-256. (in Chinese doi: 10.13675/j.cnki.tjjs.2017.02.002
LIU Yang, LI Jiang, LIU Shichang, et al. Scheme and technology investigation on solid propellant air turbo rocket[J]. Journal of Propulsion Technology, 2017, 38(2): 249-256. (in Chinese) doi: 10.13675/j.cnki.tjjs.2017.02.002
|
| [4] |
WANG H P, OLSON S J, GOLDSTEIN R J, et al. Flow visualization in a linear turbine cascade of high performance turbine blades[J]. Journal of Turbomachinery, 1997, 119(1): 1-8. doi: 10.1115/1.2841006
|
| [5] |
BENNER M W, SJOLANDER S A, MOUSTAPHA S H. The influence of leading-edge geometry on secondary losses in a turbine cascade at the design incidence[J]. Journal of Turbomachinery, 2004, 126(2): 277-287. doi: 10.1115/1.1645533
|
| [6] |
SIEVERDING C H. Recent progress in the understanding of basic aspects of secondary flows in turbine blade passages[J]. Journal of Engineering for Gas Turbines and Power, 1985, 107(2): 248-257. doi: 10.1115/1.3239704
|
| [7] |
MARKS C R, SONDERGAARD R, BEAR P S, et al. Reynolds number effects on the secondary flow of profile contoured low pressure turbines[R]. AIAA-2016-0114, 2016.
|
| [8] |
BIAN Xiutao, WANG Qingsong, CHEN Ziyu, et al. Hybrid RANS/LES study of complex turbulence characteristics and flow mechanisms on the highly-loaded turbine endwall[J]. Aerospace Science and Technology, 2019, 94: 105404. doi: 10.1016/j.ast.2019.105404
|
| [9] |
SCHREINER B D J, WILSON M, LI Y S, et al. Effect of purge on the secondary flow-field of a gas turbine blade-row[J]. Journal of Turbomachinery, 2020, 142(10): 101006. doi: 10.1115/1.4047185
|
| [10] |
魏佐君. 高负荷涡轮端区非定常流动机理及损失控制研究[D]. 西安: 西北工业大学, 2016. WEI Zuojun. Study on unsteady flow mechanism and loss control in high load turbine end zone[D]. Xi’an: Northwestern Polytechnical University, 2016. (in Chinese
WEI Zuojun. Study on unsteady flow mechanism and loss control in high load turbine end zone[D]. Xi’an: Northwestern Polytechnical University, 2016. (in Chinese)
|
| [11] |
ANANTHAKRISHNAN K, GOVARDHAN M. Influence of fillet shapes on secondary flow field in a transonic axial flow turbine stage[J]. Aerospace Science and Technology, 2018, 82: 425-437.
|
| [12] |
吕剑波, 雷志军, 孙爽, 等. 压气机叶型前缘形状对吸力面分离流动的影响[J]. 燃气轮机技术, 2015, 28(3): 24-30, 37. LVU Jianbo, LEI Zhijun, SUN Shuang, et al. Effect of leading-edge geometry on separation of high-lift compressor profile[J]. Gas Turbine Technology, 2015, 28(3): 24-30, 37. (in Chinese doi: 10.16120/j.cnki.issn1009-2889.2015.03.005
LVU Jianbo, LEI Zhijun, SUN Shuang, et al. Effect of leading-edge geometry on separation of high-lift compressor profile[J]. Gas Turbine Technology, 2015, 28(3): 24-30, 37. (in Chinese) doi: 10.16120/j.cnki.issn1009-2889.2015.03.005
|
| [13] |
李兰攀, 楚武利, 张皓光. 端壁倒圆对高负荷压气机叶栅性能及流场影响的机理探究[J]. 推进技术, 2017, 38(12): 2743-2752. LI Lanpan, CHU Wuli, ZHANG Haoguang. Mechanism study of end-wall fillet’s influence on performance and flow field of high-load compressor cascade[J]. Journal of Propulsion Technology, 2017, 38(12): 2743-2752. (in Chinese doi: 10.13675/j.cnki.tjjs.2017.12.013
LI Lanpan, CHU Wuli, ZHANG Haoguang. Mechanism study of end-wall fillet’s influence on performance and flow field of high-load compressor cascade[J]. Journal of Propulsion Technology, 2017, 38(12): 2743-2752. (in Chinese) doi: 10.13675/j.cnki.tjjs.2017.12.013
|
| [14] |
MENG Fusheng, ZHENG Qun, ZHANG Jian. Effects of blade fillet structures on flow field and surface heat transfer in a large meridional expansion turbine[J]. Energies, 2019, 12(15): 3035. doi: 10.3390/en12153035
|
| [15] |
李燕飞. 小展弦比燃气涡轮二次流动控制数值研究[D]. 哈尔滨: 哈尔滨工业大学, 2014. LI Yanfei. Numercal study on secondary flow control of the low-aspect ratio gas turbine[D]. Harbin: Harbin Institute of Technology, 2014. (in Chinese
LI Yanfei. Numercal study on secondary flow control of the low-aspect ratio gas turbine[D]. Harbin: Harbin Institute of Technology, 2014. (in Chinese)
|
| [16] |
张旭阳. 基于二次流控制的叶栅前缘端壁造型[J]. 热能动力工程, 2019, 34(8): 35-42. ZHANG Xuyang. Design of endwall in the leading edge based on the control of secondary flow[J]. Journal of Engineering for Thermal Energy and Power, 2019, 34(8): 35-42. (in Chinese doi: 10.16146/j.cnki.rndlgc.2019.08.006
ZHANG Xuyang. Design of endwall in the leading edge based on the control of secondary flow[J]. Journal of Engineering for Thermal Energy and Power, 2019, 34(8): 35-42. (in Chinese) doi: 10.16146/j.cnki.rndlgc.2019.08.006
|
| [17] |
WEI Zuojun, QIAO Weiyang, LIU Jian, et al. Reduction of endwall secondary flow losses with leading-edge fillet in a highly loaded low-pressure turbine[J]. Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy, 2016, 230(2): 184-195. doi: 10.1177/0957650915619560
|
| [18] |
TURGUT Ö H, CAMCı C. Influence of leading edge fillet and nonaxisymmetric contoured endwall on turbine NGV exit flow structure and interactions with the rim seal flow: GT2013-95842. [R]. San Antonio, US: ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, 2013.
|
DownLoad:
