Flow Mechanism and Heat Transfer Analysis on Ribbed/protruded Surface in Impingement/effusion Cooling of a Turbine Guided Vane Based on Conjugate Heat Transfer

展开
  • School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China

网络出版日期: 2026-01-05

基金资助

We would like to acknowledge the financial support for this work provided by the National Science and Technology Major Project (Grant No. J2019-III-0019-0063), and the Project from AECC Sichuan Gas Turbine Establishment (Grant No. STH-2023-0002).

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2025

Flow Mechanism and Heat Transfer Analysis on Ribbed/protruded Surface in Impingement/effusion Cooling of a Turbine Guided Vane Based on Conjugate Heat Transfer

Expand
  • School of Power and Energy, Northwestern Polytechnical University, Xi’an 710129, China

Online published: 2026-01-05

Supported by

We would like to acknowledge the financial support for this work provided by the National Science and Technology Major Project (Grant No. J2019-III-0019-0063), and the Project from AECC Sichuan Gas Turbine Establishment (Grant No. STH-2023-0002).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2025

摘要

本研究采用流固耦合数值仿真方法,对涡轮导向叶片内壁面上的不同扰流结构(即肋和凸起)的换热性能进行了系统性分析。本文深入分析了扰流结构对流动与换热的影响,包括其对压力和速度分布、努塞尔数分布以及流场结构的影响。定量分析显示,肋或凸起结构的引入可显著提高冲击孔的流量系数(最高提升71.5%)以及冷却剂与叶片内壁面之间的换热能力(最高提升47.3%),但同时会抑制气膜孔内冷却剂的排出,尤其是在采用扰流肋时。此外,各类扰流结构均对冷却剂的流动产生阻塞作用,使冷却剂消耗量最多降低2.28%。对比不同冷却结构后发现,采用直肋和凸起结构的叶片内壁面在实现较低的冷却剂消耗的同时,具有最高的综合冷却效率(最高提升0.0249)。本研究结果为涡轮叶片先进冷却结构的设计与优化提供了有价值的参考。

本文引用格式

WANG Mingrui, ZHU Huiren, YE Lin, LIU Cunliang, LI Jichen, NIU Jiajia, GUO Tao . Flow Mechanism and Heat Transfer Analysis on Ribbed/protruded Surface in Impingement/effusion Cooling of a Turbine Guided Vane Based on Conjugate Heat Transfer[J]. 热科学学报, 2026 , 35(1) : 132 -150 . DOI: 10.1007/s11630-025-2199-x

Abstract

In this study, the conjugate heat transfer method is employed to numerically investigate the thermal performance of the inner wall surface with different turbulators (i.e., ribs or protrusions) in a turbine guided vane. The effects of turbulators on flow and heat transfer are analyzed in detail, including their influence on pressure and velocity distributions, Nusselt number distributions, and flow fields. Through quantitative analysis, the results show that the introduction of ribs or protrusions dramatically increases the discharge coefficients of jet nozzles (by up to 71.5%) and the heat transfer (by up to 47.3%) between coolant and vane inner wall, while inhibiting the effusion of film holes, especially when ribs are adopted. Furthermore, all turbulators feature blockage effects on the flow of coolant, which can reduce the coolant assumption by up to 2.28%. A comparative analysis of various cooling structures reveals that the vane inner wall incorporating orthogonal ribs and protrusions exhibits the highest overall cooling effectiveness, exceeding that of the vane inner wall without turbulators by 0.0249. These findings provide valuable guidance for the design and optimization of advanced cooling structures in turbine blades.

参考文献

[1] Bunker R.S., Film cooling: Breaking the limits of diffusion shaped holes, TURBINE-09. Proceedings of International Symposium on Heat Transfer in Gas Turbine Systems, 2009.
[2] Gupta S., Chaube A., Verma P., Review on heat transfer augmentation techniques: application in gas turbine blade internal cooling. Journal of Engineering Science & Technology Review, 2012, 5(1): 57–62.
[3] Ke Z., Wang J., Conjugate heat transfer simulations of pulsed film cooling on an entire turbine vane. Applied Thermal Engineering, 2016, 109: 600–609.
[4] Wang Z., Wang D., Wang Z., et al., Heat transfer analyses of film-cooled HP turbine vane considering effects of swirl and hot streak. Applied Thermal Engineering, 2018, 142: 815–829.
[5] Kang Y.S., Rhee D.H., Lee S., et al., Conjugate heat transfer analysis to assess overall cooling effectiveness of high pressure turbine nozzle with optimized film cooling hole arrangements. Turbo Expo: Power for Land, Sea, and Air, American Society of Mechanical Engineers, 2019, 58646: V05AT10A008.
[6] Zhou W.L., Deng Q., He W., et al., Conjugate heat transfer analysis for composite cooling structure using a decoupled method. International Journal of Heat and Mass Transfer, 2020, 149: 119200.
[7] Shen Z., Xie Y., Zhang D., Numerical predictions on fluid flow and heat transfer in U-shaped channel with the combination of ribs, dimples and protrusions under rotational effects. International Journal of Heat and Mass Transfer, 2015, 80: 494–512.
[8] Rao Y., Chen P., Wan C., Experimental and numerical investigation of impingement heat transfer on the surface with micro W-shaped ribs. International Journal of Heat and Mass Transfer, 2016, 93: 683–694.
[9] Zhou J., Wang X., Li J., Influences of effusion hole diameter on impingement/effusion cooling performance at turbine blade leading edge. International Journal of Heat and Mass Transfer, 2019, 134: 1101–1118.
[10] Chang S.W., Liou H.F., Heat transfer of impinging jet-array onto concave-and convex-dimpled surfaces with effusion. International Journal of Heat and Mass Transfer, 2009, 52: 4484–4499.
[11] Hong S.K., Lee D.H., Cho H.H., Heat/mass transfer in rotating impingement/effusion cooling with rib turbulators. International Journal of Heat and Mass Transfer, 2009, 52: 3109–3117.
[12] Jing Q., Zhang D., Xie Y., Numerical investigations of impingement cooling performance on flat and non-flat targets with dimple/protrusion and triangular rib. International Journal of Heat and Mass Transfer, 2018, 126: 169–190.
[13] Cornaro C., Fleischer A.S., Goldstein R.J., Flow visualization of a round jet impinging on cylindrical surfaces. Experimental Thermal and Fluid Science, 1999, 20(2): 66–78.
[14] Rhee D.H., Nam Y.W., Cho H.H., Local heat/mass transfer with various rib arrangements in impingement/effusion cooling system with crossflow. Journal of Turbomachinery, 2004, 126(4): 615–626.
[15] Rao Y., Chen P., Wan C., Experimental and numerical investigation of impingement heat transfer on the surface with micro W-shaped ribs. International Journal of Heat and Mass Transfer, 2016, 93: 683–694.
[16] Lamont J.A., Ekkad S.V., Anne Alvin M., Effect of rotation on detailed heat transfer distribution for various rib geometries in developing channel flow. Journal of Heat Transfer, 2014, 136(1): 011901.
[17] Kumar A., Kim M.H., Thermohydraulic performance of rectangular ducts with different multiple V-rib roughness shapes: A comprehensive review and comparative study. Renewable and Sustainable Energy Reviews, 2016, 54: 635–652.
[18] Wright L.M., Fu W.L., Han J.C., Thermal performance of angled, V-shaped, and W-shaped rib turbulators in rotating rectangular cooling channels (AR=4: 1), Turbo Expo: Power for Land, Sea, and Air, 2004, 41685: 885–894.
[19] Ravi R.K., Saini R.P., Experimental investigation on performance of a double pass artificial roughened solar air heater duct having roughness elements of the combination of discrete multi V shaped and staggered ribs. Energy, 2016, 116: 507–516.
[20] Ekkad S.V., Huang Y., Han J.C., Detailed heat transfer distributions in two-pass square channels with rib turbulators and bleed holes. International Journal of Heat and Mass Transfer, 1998, 41(23): 3781–3791.
[21] Fu W.L., Wright L.M., Han J.C., Heat transfer in two-pass rotating rectangular channels (AR=2: 1) with discrete ribs. Journal of Thermophysics and Heat Transfer, 2006, 20(3): 569–582.
[22] Chen Y., Chew Y.T., Khoo B.C., Heat transfer and flow structure in turbulent channel flow over protrusions. International Journal of Heat and Mass Transfer, 2013, 66: 177–191.
[23] Du W., Luo L., Wang S., et al., Flow structure and heat transfer characteristics in a 90-deg turned pin fined duct with different dimple/protrusion depths. Applied Thermal Engineering, 2019, 146: 826–842.
[24] Kim J.E., Doo J.H., Ha M.Y., et al., Numerical study on characteristics of flow and heat transfer in a cooling passage with protrusion-in-dimple surface. International Journal of Heat and Mass Transfer, 2012, 55: 7257–7267.
[25] Kaur I., Singh P., Ekkad S.V., Enhanced thermal hydraulic performance by V-shaped protrusion for gas turbine blade trailing edge cooling. International Journal of Heat and Mass Transfer, 2020, 149: 119221.
[26] Xie Y., Qu H., Zhang D., Numerical investigation of flow and heat transfer in rectangular channel with teardrop dimple/protrusion. International Journal of Heat and Mass Transfer, 2015, 84: 486–496.
[27] Wang M.R., Zhu H.R., Liu C.L., et al., Numerical analysis and design optimization on full coverage film-cooling for turbine guided vane. Engineering Applications of Computational Fluid Mechanics, 2022, 16(1): 904–936.
[28] Wang M.R., Zhu H.R., Liu C.L., et al., Numerical investigation of flow and heat transfer in vane impingement/effusion cooling with various rib/dimple structure. Journal of Thermal Science, 2023, 32(4): 1357–1377.
[29] Wang M.R., Zhu H.R., Liu C.L., et al., Structure improvement on turbine guided vane cooling system based on conjugate heat transfer. International Journal of Thermal Sciences, 2022, 172: 107332.
[30] Huang Y., Zhang J., Wang C., Shape-optimization of round-to-slot holes for improving film cooling effectiveness on a flat surface. Heat and Mass Transfer, 2018, 54(6): 1741–1754.
[31] Andrews G.E., Asere A.A., Mkpadi M.C., et al., Transpiration cooling: contribution of film cooling to the overall cooling effectiveness. International Journal of Turbo and Jet Engines, 1986, 3(2–3): 245–256.
文章导航

/