English

Journal of Thermal Science

热科学学报

热科学学报 >

2022 , Vol. 31 >Issue 5: 1696 - 1708

DOI: https://doi.org/10.1007/s11630-022-1595-8

气动

Cooling Performance of the Endwall Vertical Hole Considering the Interaction between Cooling Jet and Leading-Edge Horseshoe Vortex

  • CHEN Ziyu ,
  • SU Xinrong ,
  • YUAN Xin
展开
  • Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Tsinghua University, Beijing 100084, China

网络出版日期: 2023-12-01

基金资助

This work is supported by the National Natural Science Foundation of China (Grant No. 51876098) and National Science and Technology Major Project (2017-III-0009-0035). This research is also sponsored by the Tsinghua University Initiative Scientific Research Program.

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022
收起

Cooling Performance of the Endwall Vertical Hole Considering the Interaction between Cooling Jet and Leading-Edge Horseshoe Vortex

  • CHEN Ziyu ,
  • SU Xinrong ,
  • YUAN Xin
Expand
  • Key Laboratory for Thermal Science and Power Engineering of Ministry of Education, Tsinghua University, Beijing 100084, China

Online published: 2023-12-01

Supported by

This work is supported by the National Natural Science Foundation of China (Grant No. 51876098) and National Science and Technology Major Project (2017-III-0009-0035). This research is also sponsored by the Tsinghua University Initiative Scientific Research Program.

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2022
Fold

摘要

冷气与二次流的交互作用显著影响着端区的冷却效果。在叶根前缘区域，进口边界层内部的流体回卷形成了马蹄涡。马蹄涡卷吸冷气进入主流，为前缘附近端区的冷却设计带来了严峻的挑战。本文探究了前缘马蹄涡的生成机制，在此基础上发展了新型的垂直孔冷却设计。当射流动量比足够高时，冷气能够越过马蹄涡直接冲击叶片表面，并在压力梯度的作用下，均匀地覆盖在前缘滞止区。本文采用数值模拟的办法，首先对比了圆孔和方孔的冷却效果，发现后者由于其更高的射流刚度和非对称的涡结构，取得了更好的冷却覆盖。通过探究冷却效果对吹风比的敏感性，结果表明，当吹风比等于2.0时，能够在叶根处端区取得最高的平均气膜有效度，而叶片角区的冷却效果则随着吹风比的增加单调地升高。此外，还观察到了由于冷气受到端区横流裹挟在叶片吸力面的三角区域形成的二次冷却现象。

关键词： film cooling; leading edge; secondary flow; horseshoe vortex

本文引用格式

CHEN Ziyu , SU Xinrong , YUAN Xin . Cooling Performance of the Endwall Vertical Hole Considering the Interaction between Cooling Jet and Leading-Edge Horseshoe Vortex[J]. 热科学学报, 2022 , 31(5) : 1696 -1708 . DOI: 10.1007/s11630-022-1595-8

Abstract

Interaction between the coolant and the secondary flow plays an important role in endwall cooling performance. For the leading-edge region, oncoming main flow inside the boundary layer impinges onto the vane leading edge and turns into the horseshoe vortex. Horseshoe vortex entrains coolant off the surface, thus posing severe challenges to the cooling design there. Based on analyses on the leading-edge vortex formation mechanism, a new kind of endwall film cooling design, vertical hole upstream of the saddle point, is proposed to obtain more uniform film coverage over the vane/endwall junction region. Coolant injected from the vertical hole can pass over the horseshoe vortex and impinge around the stagnation line on the vane leading edge. Uniform film coverage can be obtained around the vane leading edge where coolant clings to the endwall surface due to the span-wise pressure gradient of the stagnation region. Numerical simulations are conducted about the cooling performance of two main kinds of both isotropic and anisotropic hole geometries for the endwall and vane surface. Results come that the anisotropic hole shows significant advantages over the isotropic one because it suppresses the symmetrical kidney vortices thus weakening the mixture with high-temperature gas. Blowing ratio (M) effect is analyzed and conclusions are drawn that the cooling performance of the endwall around the leading edge is sensitive to M and adiabatic film cooling effectiveness peaks at about M = 2.0. Better cooling performance over the vane corner region can be obtained when M gets even higher while the effective film coverage area shrinks. Apart from that, the phenomenon of phantom cooling on the upper triangular region of the suction surface can be observed when coolant on the endwall is entrained by the vortex formed at the corner of the leading edge.

Key words： film cooling; leading edge; secondary flow; horseshoe vortex

参考文献

[1] Bogard D.G., Thole K.A., Gas turbine film cooling. Journal of Propulsion and Power, 2006, 22(2): 249–270.
[2] Zhang H., Li Y., Chen Z., Su X., Yuan X., Multi-fidelity model based optimization of shaped film cooling hole and experimental validation. International Journal of Heat and Mass Transfer, 2019, 132: 118–129.
[3] An B.T., Liu J., Zhou S., Geometrical parameter effects on film cooling effectiveness of rectangular diffusion holes. Journal of Turbomachinery, 2017, 139: 081010.
[4] Liu J.J., Lin X.C., Zhang X.D., et al., Investigation on cooling effectiveness and aerodynamic loss of a turbine cascade with film cooling. Journal of Thermal Science, 2016, 25(1): 50–59.
[5] Liu J.J., An B.T., Liu J., Zhan W., Leading edge film cooling enhancement for an inlet guide vane with fan-shaped holes. Journal of Thermal Science, 2010, 19(6): 514–518.
[6] Wang H., Tao Z., Li H., A tip region film cooling study of the fan-shaped hole using PSP. International Journal of Heat and Mass Transfer, 2020, 153: 119378.
[7] Fu Z., Zhu H., Liu C., Wei J., Zhang B., Investigation of the influence of inclination angle and diffusion angle on the film cooling performance of chevron shaped hole. Journal of Thermal Science, 2018, 27(6): 78–89.
[8] Luo J., Mcbean I., Liu F., Optimization of endwall contours of a turbine blade row using an adjoint method. ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, 2011, June 6–10, 2011, Vancouver, British Columbia, Canada, Volume 7: Turbomachinery, Parts A, B, and C, Paper No. GT2011-46163.
[9] Langston L.S., Crossflows in a turbine cascade passage. Journal of Engineering for Power, 1980, 102(4): 866– 874.
[10] Langston L.S., Secondary flows in axial turbines-a review. Annals of the New York Academy of Sciences, 2001, 934(1): 11–26.
[11] Sieverding C.H., Recent progress in the understanding of basic aspects of secondary flows in turbine blade passages. Journal of Engineering for Gas Turbines and Power, 1985, 102(2): 248–257.
[12] Sharma O.P., Butler T.L., Predictions of endwall losses and secondary flows in axial flow turbine cascades. ASME 1986 International Gas Turbine Conference and Exhibit, 1986, Paper No. V001T01A098.
[13] Wang H.P., Olson S.J., Goldstein R.J., Eckert E.R., Flow visualization in a linear turbine cascade of high-performance turbine blades. Journal of Turbomachinery, 1997, 119(1): 1–8.
[14] Bear P., Wolff M., Gross A., Marks C.R., Sondergaard R., Experimental investigation of total pressure loss development in a highly loaded low-pressure turbine cascade. Journal of Turbomachinery, 2018, 140(3): 031003.
[15] Friedrichs S., Hodson H.P., Dawes W.N., Distribution of film-cooling effectiveness on a turbine endwall measured using the ammonia and diazo technique. ASME 1995 International Gas Turbine and Aeroengine Congress and Exposition, 1995, June, Paper No. V004T09A001.
[16] Friedrichs S., Hodson H.P., Dawes W.N., Aerodynamic aspects of endwall film-cooling. Journal of Turbomachinery, 1997, 119(4): 786–793.
[17] Friedrichs S., Hodson H.P., Dawes W.N., The design of an improved endwall film-cooling configuration. ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition, 1998, Paper No. V004T09A082.
[18] Jabbari M.Y., Marston K.C., Eckert R.G., Goldstein R.J., Film cooling of the gas turbine endwall by discrete-hole injection. Journal of Turbomachinery, 1996, 118(2): 278–284.
[19] Thomas M., Kirollos B., Jackson D., Povey T., Experimental and CFD studies of NGV endwall cooling. ASME Turbo Expo 2013, Turbine Technical Conference and Exposition, 2013, Paper No. V03BT13A056.
[20] Ornano F., Povey T., Experimental and computational study of the effect of momentum-flux ratio on high-pressure nozzle guide vane endwall cooling systems. Journal of Turbomachinery, 2017, 139(12): 121002.
[21] Thrift A.A., Thole K.A., Hada S., Effects of orientation and position of the combustor-turbine interface on the cooling of a vane endwall. ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, 2011, Volume 5: Heat Transfer, Parts A and B, Paper No. GT2011-45507.
[22] Knost D.G., Thole K.A., Computational predictions of endwall film-cooling for a first stage vane. In ASME Turbo Expo 2003, collocated with the 2003 International Joint Power Generation Conference, 2003, Volume 5: Turbo Expo 2003, Parts A and B, Paper No. GT2003-38252.
[23] Thole K.A., Knost D.G., Heat transfer and film-cooling for the endwall of a first stage turbine vane. International Journal of Heat and Mass Transfer, 2005, 48(25–26): 5255–5269.
[24] Knost D.G., Thole K.A., Adiabatic effectiveness measurements of endwall film-cooling for a first stage vane. ASME Turbo Expo 2004: Power for Land, Sea, and Air, 2004, Volume 3: Turbo Expo 2004, Paper No. GT2004-53326.
[25] Wright L.M., Blake S.A., Han J.C., Film cooling effectiveness distributions on a turbine blade cascade platform with stator-rotor purge and discrete film hole flows. Journal of Turbomachinery, 2006, 130(3): 383– 394.
[26] Chen A.F., Shiau C.C., Han J.C., Turbine blade platform film cooling with fan-shaped holes under simulated swirl purge flow and slash face leakage conditions. Journal of Turbomachinery, 2018, 140(4): 011006.
[27] Papa M., Srinivasan V., Goldstein R.J., Film cooling effect of rotor-stator purge flow on endwall heat/mass transfer. Journal of Turbomachinery, 2012, 134: 1729– 1738.
[28] Zhang Y., Yuan X., Experimental investigation of turbine phantom cooling on suction side with combustor-turbine leakage gap flow and endwall film cooling. ASME Turbo Expo 2012: Turbine Technical Conference and Exposition, 2012, Volume 4: Heat Transfer, Parts A and B, Paper No. GT2012-69295.
[29] Zhang Y., Li Y., Yuan X., Effects of inlet swirl on suction side phantom cooling. ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, 2016, Paper No. V05CT19A027.
[30] Zhang Y., Li Y., Yuan X., Turbine endwall film cooling with combustor-turbine interface gap leakage flow: Effect of incidence angle. Journal of Thermal Science, 2013, 22(2): 135–144.
[31] Zhang L., Yin J., Liu K., Hee-Koo M., Effect of hole diameter on nozzle endwall film cooling and associated phantom cooling. ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, 2015, Paper No. V05BT12A016.
[32] Li S.J., Lee J., Han J.C., Zhang L., Moon H.K., Turbine platform cooling and blade suction surface phantom cooling from simulated swirl purge flow. Journal of Turbomachinery, 2016, 138(8): 081004.
[33] Zhang Y., Yuan X., Turbine endwall film cooling with pressure side radial holes. ASME Turbo Expo 2013: Turbine Technical Conference and Exposition, 2013, Paper No. V03BT13A049.
[34] Li S.J., Yang S.F., Han J.C., Zhang L., Moon H.K., Turbine blade surface phantom cooling from upstream nozzle trailing edge ejection. In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, 2015, Paper No. V05BT12A003.
[35] Zhang L., Yin J., Moon H.K., The effects of vane showerhead injection angle and film compound angle on nozzle endwall cooling (phantom cooling). Journal of Turbomachinery, 2015, 137(2): 021003.
[36] Li X., Ren J., Jiang H., Phantom cooling of nozzle trailing edge discharge on blade surface and platform. In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, 2014, Paper No. V05BT13A010.
[37] Sundaram N., Thole K.A., Bump and trench modifications to film-cooling holes at the vane-endwall junction. Journal of Turbomachinery, 2008, 130(4): 041013.
[38] Du K., Song L., Li J., Sunden B., Effects of the layout of film holes near the vane leading edge on the endwall cooling and phantom cooling of the vane suction side surface. Numerical Heat Transfer Part A Applications, 2017, 71(9): 910–927.
[39] Du K., Song L., Li J., Sunden B., Effects of the mainstream turbulence intensity and slot injection angle on the endwall cooling and phantom cooling of the vane suction side surface. International Journal of Heat & Mass Transfer, 2017, 112: 427–440.
[40] Kenichiro T., Yutaka O., Junichi S., Shitaro K., Effect of endwall film cooling upstream an airfoil/endwall junction to suppress the formation of horseshoe vortex in a symmetric airfoil. ASME Turbo Expo: Turbine Technical Conference and Exposition. 2013, Paper No. V03BT13A052.
[41] Zhou Y., Zhang Y., Su X., Yuan X., Effect of inlet rotating swirl on endwall film cooling for two representative hole arrangements. Chinese Journal of Aeronautics, 2018, 31(5): 1095–1108.
[42] Leach K.P., Energy efficient engine high-pressure turbine component rig performance test report. NASA Report, 1983, Report No. NASA-CR-168189.
Options
文章导航

/

〈 〉

微信公众号

主办单位：中国科学院工程热物理研究所　 出版单位：科学出版社

版权所有© 2023 热科学学报