CST造型方法在涡轮叶片前缘修型中的应用研究

doi:10.13675/j.cnki. tjjs. 190063

推进技术 ›› 2019, Vol. 40 ›› Issue (8): 1767-1779.DOI: 10.13675/j.cnki. tjjs. 190063

CST造型方法在涡轮叶片前缘修型中的应用研究

哈尔滨工业大学能源科学与工程学院

发布日期:2021-08-15
作者简介:崔涛，博士生，研究领域为叶轮机械气动热力学。E-mail：cui.tao.1988@163.com
基金资助:
国家自然科学基金 51206034 51436002国家自然科学基金（51206034；51436002）。

Application of CST Method on Modifying Leading Edgeof Axial-Flow Turbine Blade

School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

Published:2021-08-15

摘要/Abstract

摘要： 为了探究CST(形状函数变换技术)造型方法在涡轮叶片前缘修型中的应用效果，完善了CST方法在前缘型线重构中的实施细节，数值模拟了雷诺数对前缘修型前后叶型损失及边界层特性的影响，验证了CST前缘修型方法在新型高速飞行器低压涡轮中的实用性。结果显示：CST方法前缘修型可以消除HD叶型吸力侧前缘的压力峰和分离泡，从而使得高雷诺数条件下吸力侧分离诱导的边界层转捩现象延迟发生，叶型损失降低32%，拓展了低损失状态的雷诺数范围。吸力侧损失的降低在低雷诺数条件下主要来自于前缘附近的剪切层，而高雷诺数条件下主要来自于前缘剪切层和扩压段前的层流边界层。新型高速空天飞行器低压涡轮叶片采用CST前缘修型对提升效率是有效的，在设计点状态附近效率提高0.1%，而膨胀比较低的大负攻角状态下效率提升0.3%~0.5%，损失降低的位置主要集中在叶展中部压力侧边界层和根部的二次流区域。

关键词: 涡轮;前缘;压力尖峰;分离泡;边界层;叶型损失;能量耗散;熵产率

Abstract: In order to explore the effects of leading edge modified with the method of CST (Class Function/Shape Function Transformation Technique) on the aerodynamic performance of the blade profile， firstly, the implementation details of CST method in leading edge reconstruction are improved. Secondly, the effects of Reynolds number on profile losses and boundary layer characteristics are studied with numerical simulation. Finally, the practicability of the CST leading edge modification method is verified in the low-pressure turbine of a new high-speed aircraft. The results show that the CST method can eliminate the pressure spike and separation bubble near the suction leading edge of HD profile, which also delays the transition phenomenon induced by the suction leading edge separation bubble under high Reynolds number condition and expands the range of low-loss state Reynolds number. In addition, the profile loss is reduced by 32%. The reduction of suction profile loss under low Reynolds number condition is mainly from the shear layer near the leading edge, while the reduction of suction profile loss under high Reynolds number is mainly from the shear layer near the leading edge and the laminar boundary layer before diffuser section. The application of CST leading edge modification in high-speed aerospace vehicle low-pressure turbine rotor is verified to be effective on improving the aerodynamics efficiency, that making a contribution to increasing the efficiency by 0.1% around the design point and about 0.3%~0.5% at lower expansion state with large negative incidence. The position where the loss is reduced is mainly concentrated in the boundary layer of pressure side and the secondary flow region near the root.

Key words: Turbine;Leading edge;Pressure spike;Separation bubble;Boundary layer;Profile loss;Energy dissipation;Entropy production rate

. CST造型方法在涡轮叶片前缘修型中的应用研究[J]. 推进技术, 2019, 40(8): 1767-1779.

参考文献

[1] Goodhand M N， Miller R J. The Impact of Real Geometries on Three-Dimensional Separations in Compressors[J]. Journal of Turbomachinery， 2012， 134(2).
[2] 陈雷，陈江，赵石磊，等. 叶片前缘形状对涡轮气动性能的影响[J]. 航空动力学报， 2013， 28(4): 921-929.
[3] 杨炯，宁涛，席平. 前缘点曲率可控的曲率连续前缘几何设计[J]. 计算机辅助设计与图形学学报， 2016， 28(7): 1195-1200.
[4] 陈智. 曲率连续前缘对压气机静叶气动性能的影响研究[D]. 大连：大连海事大学， 2018.
[5] Hamakhan I A， Korakianitis T. Aerodynamic Performance Effects of Leading-Edge Geometry in Gas-Turbine Blades[J]. Applied Energy， 2010， 87(5): 1591-1601.
[6] Hodson H P. Boundary-Layer Transition and Separation Near the Leading Edge of a High-Speed Turbine Blade[J]. Journal of Engineering for Gas Turbines and Power， 1985， 107(1): 127-134.
[7] 陆宏志，吴洋洲，陆利蓬，等. 压气机叶片前缘楔形角对前缘分离泡的影响[J]. 工程热物理学报， 2002(5): 569-572.
[8] 陆宏志，徐力平. 压气机叶片的带平台圆弧形前缘[J]. 推进技术， 2003， 24(6): 532-536. (LU Hong-zhi， XU Li-ping. Circular Leading Edge with a Flat for Compressor Blades[J]. Journal of Propulsion Technology， 2003， 24(6): 532-536.)
[9] Benner M W， Sjolander S A， Moustapha S H. Influence of Leading-Edge Geometry on Profile Losses in Turbines at Off-Design Incidence: Experimental Results and an Improved Correlation[J]. Journal of Turbomachinery， 1997， 119(2): 193-200.
[10] 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.
[11] Carter A D S. Blade Profiles for Axial Flow Fans， Pumps， Compressors， etc[J]. Proceedings of the Institution of Mechanical Engineers， 1961， 175(1): 775-806.
[12] Walraevens R E， Cumpsty N A. Leading Edge Separation Bubbles on Turbomachine Blades[J]. Journal of Turbomachinery， 1995， 117(1): 115-125.
[13] Wheeler A P S， Sofia A， Miller R J. The Effect of Leading-Edge Geometry on Wake Interactions in Compressors[J]. Journal of Turbomachinery， 2009， 131(4).
[14] Goodhand M N， Miller R J. Compressor Leading Edge Spikes: a New Performance Criterion[J]. Journal of Turbomachinery， 2010， 132(2).
[15] Zhang W， Zou Z， Ye J. Leading-Edge Redesign of a Turbomachinery Blade and Its Effect on Aerodynamic Performance[J]. Applied Energy， 2012， 93: 655-667.
[16] 刘宝杰，袁春香，于贤君. 前缘形状对可控扩散叶型性能影响[J]. 推进技术， 2013， 34(7): 890-897. (LIU Bao-jie， YUAN Chun-xiang， YU Xian-jun. Effects of Leading-Edge Geometry on Aerodynamic Performance in Controlled Diffusion Airfoil[J]. Journal of Propulsion Technology， 2013， 34(7): 890-897.)
[17] 宋寅，顾春伟. 曲率连续的压气机叶片前缘设计方法[J]. 推进技术， 2013， 34(11): 1474-1481. (SONG Yin， GU Chun-wei. Effects of Leading-Edge Geometry on Aerodynamic Performance in Controlled Diffusion Airfoil[J]. Journal of Propulsion Technology， 2013， 34(11): 1474-1481.)
[18] Song Y， Gu C W， Xiao Y B. Numerical and Theoretical Investigations Concerning the Continuous-Surface-Curvature Effect in Compressor Blades[J]. Energies， 2014， 7: 8150-8177.
[19] Song Y， Gu C W. Effects of Curvature Continuity of Compressor Blade Profiles on Their Performances[R]. ASME GT2014-25804.
[20] 白涛，邹正平，张伟昊，等. 前缘形状对涡轮叶栅损失影响的机理[J]. 航空动力学报， 2014， 29(6): 1482-1489.
[21] 张小龙，姜斌，郑群，等. 压气机叶片前缘形状与局部损失相关性[J]. 哈尔滨工程大学学报， 2015， 36(4).
[22] 于贤君，朱宏伟，刘宝杰. 亚音叶型前缘形状对附面层参数影响[J]. 工程热物理学报， 2017， 38(10): 2108-2118.
[23] 杨凌，李勇俊，钟兢军. 前缘复合改型在压气机平面叶栅中的应用初探[J]. 推进技术， 2019， 40(1): 121-128. (YANG Ling， LI Yong-jun， ZHONG Jing-jun. Preliminary Investigation of Elliptic Tubercle Leading Edge Blade in Planar Compressor Cascade[J]. Journal of Propulsion Technology， 2019， 40(1): 121-128.)
[24] Pritchard L J. An Eleven Parameter Axial Turbine Airfoil Geometry Model[R]. ASME 85-GT-219.
[25] Kulfan B M， Bussoletti J E. Fundamental Parametric Geometry Representations for Aircraft Component Shapes[R]. AIAA2006-6948.
[26] Kulfan B M. A Universal Parametric Geometry Representation Method-“CST”[R]. AIAA2007-62.
[27] Hodson H P， Dominy R G. The Off-Design Performance of a Low-Pressure Turbine Cascade[J]. Journal of Turbomachinery， 1987， 109(2): 201-209.
[28] Hodson H P， Dominy R G. Three-Dimensional Flow in a Low-Pressure Turbine Cascade at Its Design Condition[J]. Journal of Turbomachinery， 1987， 109(2): 177-185.
[29] 朱俊强，屈骁，张燕峰，等. 高负荷低压涡轮内部非定常流动机理及其控制策略研究进展[J]. 推进技术， 2017， 38(10): 2186-2199.
[30] Howard P H， Robert J H. The Role of Transition in High-Lift Low-Pressure Turbines for Aeroengines[J]. Progress in Aerospace Sciences， 2005， 41(6): 419-454.
[31] Mayle R E. The Role of Laminar-Turbulent Transition in Gas Turbine Engines [J]. Journal of Turbomachinery， 1991， 113(2): 207-216.
[32] 张银波，郑伟. 雷诺数对低压涡轮附面层转捩影响的数值研究[J]. 燃气涡轮试验与研究， 2015， 28(2).
[33] 邹正平，宁方飞，刘火星，等. 雷诺数对涡轮叶栅流动的影响[J]. 工程热物理学报， 2004， (2): 216-219.
[34] 梁赟，刘火星，邹正平. 高负荷低压涡轮边界层转捩的实验研究[J]. 推进技术， 2017， 38(5): 1023-1029. (LIANG Yun， LIU Huo-xing， ZOU Zheng-ping. Experimental Investigation on Boundary Layer Transition Process in High-Lift Low-Pressure Turbines[J]. Journal of Propulsion Technology， 2017， 38(5): 1023-1029.)
[35] 冯涛，程洪贵，杨琳，等. 边界层特性对雷诺数变化的敏感性分析[J]. 推进技术， 2005， 26(4): 328-334.
[36] Curtis E M， Hodson H P， Banieghbal M R， et al. Development of Blade Profiles for Low-Pressure Turbine Applications[J]. Journal of Turbomachinery， 1997， 119(3): 531-538.
[37] Denton J D. Loss Mechanisms in Turbomachines[J]. Journal of Turbomachinery， 1993， 115(4): 621-656.
[38] Li Z， Du J， Ottavy X， et al. Quantification and Analysis of the Irreversible Flow Loss in a Linear Compressor Cascade[J]. Entropy， 2018， 20(7).
[39] 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.
[40] Greitzer E M， Graf M B， Tan C S， et al. Internal Flow: Concepts and Applications[M]. Cambridge： Cambridge University Press， 2007.

CST造型方法在涡轮叶片前缘修型中的应用研究

Application of CST Method on Modifying Leading Edgeof Axial-Flow Turbine Blade

PDF

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 0

编辑推荐

Metrics

本文评价