Fluid Mechanics and Flight Mechanics

Effects of low-pressure turbine rig test method on measurement accuracy of efficiency

  • Lei ZHAO ,
  • Jie LI ,
  • Jingying XU
Expand
  • Turbine Department,AECC Commercial Aircraft Engine Co. ?,Ltd. ,Shanghai 200241,China

Received date: 2024-09-02

  Revised date: 2024-09-20

  Accepted date: 2024-11-19

  Online published: 2024-11-25

Abstract

Turbine rig test is a most important way to evaluate the turbine component performance. In the test, the accuracy of efficiency measurement is very important to the test results, but will be affected by many process factors. Based on the results of low-pressure turbine rig test, this paper analyzes the effects of inlet and outlet flow field, sealing flow temperature/mass flow rate, Reynolds number, tip clearance, mechanical loss and efficiency definition on turbine test efficiency, so as to provide reference for turbine performance test scheme design, instrumentation design and test data analysis. The uniformity of inlet total temperature can be improved by setting the sealing flow to have the same temperature as the main flow and covering the inlet outer casing with thermal insulation material during test. The circumferential distribution of the turbine exit measurement points is strongly correlated with the phase of the last guide vane. The circumferential arrangement of the exit probe should consider the influences of the wake and main flow regions of the last guide vane; otherwise, an efficiency deviation exceeding 0.1% may occur. The influences of the sealing flow temperature ratio and flow ratio on the turbine efficiency must be considered and strictly controlled in the turbine test. For a low-pressure turbine, the efficiency decreases by 0.11% with 0.1 increase in the seal air temperature ratio, and by 0.29% with 1% increase in the mass flow rate. The Reynolds number has a significant impact on the efficiency of the low-pressure tur-bine. When collecting turbine map data by using the scheme with a fixed exit total pressure, the difference in low-pressure turbine efficiency caused by change of Reynolds number can reach 1%. Turbine map tests should be conducted at the Reynolds number that is above the self-simulation region or is equal for different test conditions, or the effect of Reynolds number could be corrected after the test. In addition, this paper also shows the effect of blade tip clearance, mechanical losses, and efficiency definition on test efficiency.

Cite this article

Lei ZHAO , Jie LI , Jingying XU . Effects of low-pressure turbine rig test method on measurement accuracy of efficiency[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2025 , 46(15) : 131142 -131142 . DOI: 10.7527/S1000-6893.2024.31142

References

[1] HOWELL R J. Wake-separation bubble interactions in low Reynolds number turbomachinery[D]. Cambridge, East of England: University of Cambridge, 1999.
[2] HOWELL R J, RAMESH O N, HODSON H P, et al. High lift and aft-loaded profiles for low-pressure turbines[J]. Journal of Turbomachinery2001123(2): 181-188.
[3] 卫刚, 王永明, 王松涛, 等. 高性能低压涡轮设计与试验[J]. 燃气涡轮试验与研究201326(2): 6-11.
  WEI G, WANG Y M, WANG S T, et al. Design and experiment of a high performance low-pressure turbine[J]. Gas Turbine Experiment and Research201326(2): 6-11 (in Chinese).
[4] HASELBACH F, SCHIFFER H P, HORSMAN M, et al. The application of ultra high lift blading in the BR715 LP turbine?[J]. Journal of Turbomachinery2002124(1): 45-51.
[5] HARVEY N W, BRENNAN G, NEWMAN D A, et al. Improving turbine efficiency using non-axisymmetric end walls: Validation in the multi-row environment and with low aspect ratio blading?[C]?∥ASME Turbo Expo 2002: Power for Land, Sea, and Air, 2009: 119-126.
[6] BRENNAN G, HARVEY N W, ROSE M G, et al. Improving the efficiency of the Trent 500-HP turbine using nonaxisymmetric end walls (part Ⅰ): Turbine design[J]. Journal of Turbomachinery2003125(3): 497-504.
[7] ROSE M G, HARVEY N W, SEAMAN P, et al. Improving the efficiency of the Trent 500 HP turbine using non-axisymmetric end walls (part Ⅱ): Experimental validation[C]?∥ASME Turbo Expo 2001: Power for Land, Sea, and Air, 2014.
[8] GERMAIN T, NAGEL M, Ⅰ RAAB, et al. Improving efficiency of a high work turbine using non-axisymmetric endwalls (Part I): Endwall design and performance[C]?∥ASME Turbo Expo 2008: Power for Land, Sea, and Air, 2009: 1109-1119.
[9] JOUINI D B M, LITTLE D, BANCALARI E, et al. Experimental investigation of airfoil wake clocking impacts on aerodynamic performance in a two stage turbine test rig[C]?∥ASME Turbo Expo 2003, Collocated with the 2003 International Joint Power Generation Conference, 2009: 351-358.
[10] 中国航空工业集团公司. 航空燃气涡轮发动机轴流涡轮气动性能试验方法: [S]. 北京: 中国航空综合技术研究所, 2013.
  Aviation Industry Corporation of China. Aerodynamic performance test method of axial turbine for aircraft gas turbine engine: ?[S]. Beijing: AVIC China Aero-Polytechnology Establishment, 2013 (in Chinese).
[11] 安兆强, 陈强, 郝晟淳, 等. 大涵道比发动机多级低压涡轮试验技术研究[J]. 航空发动机201844(6): 69-73.
  AN Z Q, CHEN Q, HAO S C, et al. Research on multistage low pressure turbine test technology for high bypass ratio aeroengine?[J]. Aeroengine201844(6): 69-73 (in Chinese).
[12] 邸亚超, 胡应交, 张星, 等. 涡轮试验准则数对流场相似性的影响[J]. 航空动力学报201833(1): 193-200.
  DI Y C, HU Y J, ZHANG X, et al. Influence of turbine test criterion parameters on flow similarity[J]. Journal of Aerospace Power201833(1): 193-200 (in Chinese).
[13] 杨帆. 涡轮轮缘封严气流与主流非定常干涉机理及其损失控制研究[D]. 西安: 西北工业大学, 2019: 35-65.
  YANG F. Investigation of unsteady interaction mechanism and associated loss control between turbine rim seal flow and mainstream[D]. Xi’an: Northwestern Polytechnical University, 2019: 35-65 (in Chinese).
[14] 张剑. 叶尖间隙对涡轮性能影响的计算与试验研究[J]. 燃气涡轮试验与研究201225(2): 33-36.
  ZHANG J. Calculation and test of influence of rotor tip clearance on turbine performance[J]. Gas Turbine Experiment and Research201225(2): 33-36 (in Chinese).
[15] 王松涛, 刘勋, 周逊, 等. 低压涡轮低雷诺数条件下气动性能分析[J]. 汽轮机技术201153(5): 324-327.
  WANG S T, LIU X, ZHOU X, et al. Aerodynamic performance analysis of low pressure turbine at low Reynolds numbers[J]. Turbine Technology201153(5): 324-327 (in Chinese).
[16] REID K, DENTON J, PULLAN G, et al. The effect of stator-rotor hub sealing flow on the mainstream aerodynamics of a turbine?[C]?∥ASME Turbo Expo 2006: Power for Land, Sea, and Air, 2008: 789-798.
[17] SCHUEPBACH P, ABHARI R S, ROSE M G, et al. Effects of suction and injection purge-flow on the secondary flow structures of a high-work turbine[J]. Journal of Turbomachinery2010132(2): 021021.
[18] REGINA K, KALFAS A I, ABHARI R S. Experimental investigation of purge flow effects on a high pressure turbine stage[J]. Journal of Turbomachinery2015137(4): 041006.
[19] 邹正平, 王松涛, 刘火星, 等. 航空燃气轮机涡轮气体动力学: 流动机理及气动设计[M]. 上海: 上海交通大学出版社, 2014: 183-192.
  ZOU Z P, WANG S T, LIU H X, et al. Turbine aerodynamics for aero-engine?[M]. Shanghai: Shanghai Jiao Tong University Press, 2014: 183-192 (in Chinese).
[20] VOLINO R J, HULTGREN L S. Measurements in separated and transitional boundary layers under low-pressure turbine airfoil conditions?[J]. Journal of Turbomachinery2001123(2): 189-197.
[21] HODSON H P, HOWELL R J. The role of transition in high-lift low-pressure turbines for aeroengines[J]. Progress in Aerospace Sciences200541(6): 419-454.
[22] 张天龙, 陈强, 赵展, 等. 雷诺数对高负荷低速涡轮性能影响的试验研究[J]. 测控技术202443(2): 74-79.
  ZHANG T L, CHEN Q, ZHAO Z, et al. Experimental study on the effect of Reynolds number on the performance of high-load low-speed turbines[J]. Measurement & Control Technology202443(2): 74-79 (in Chinese).
[23] BRINGHENTI C, BARBOSA J R. Effects of turbine tip clearance on gas turbine performance?[C]?∥ASME Turbo Expo 2008: Power for Land, Sea, and Air, 2009: 1715-1721.
[24] 谷雪花, 郝晟淳, 张东海, 等. 叶尖间隙对涡轮性能影响的试验研究[J]. 航空发动机202046(4): 78-81.
  GU X H, HAO S C, ZHANG D H, et al. Experimental study on influence of tip clearance on turbine performance[J]. Aeroengine202046(4): 78-81 (in Chinese).
[25] YOON S, CURTIS E, DENTON J, et al. The effect of clearance on shrouded and unshrouded turbines at two levels of reaction[C]?∥ASME Turbo Expo 2010: Power for Land, Sea, and Air, 2010: 1231-1241.
Outlines

/