叶片反扭对跨声速大涵道比风扇性能的影响

杨慧; 沈真; 郑赟

doi:10.13224/j.cnki.jasp.2016.01.014

叶片反扭对跨声速大涵道比风扇性能的影响

doi: 10.13224/j.cnki.jasp.2016.01.014

杨慧^1,2,
沈真^1,2,
郑赟^1,2

1. 北京航空航天大学能源与动力工程学院, 北京 100191;
2. 先进航空发动机协同创新中心, 北京 100191

详细信息

作者简介:
杨慧(1970-),女,安徽阜阳人,讲师,博士,主要从事叶轮机械气动弹性数值模拟和试验研究.

中图分类号: V232.4
计量
- 文章访问数: 832
- HTML浏览量: 1
- PDF量: 512
- 被引次数: 0
出版历程
- 收稿日期: 2014-05-16
- 刊出日期: 2016-01-28

Influence of blade untwist on transonic high bypass ratio fan performance

YANG Hui^1,2,
SHEN Zhen^1,2,
ZHENG Yun^1,2

1. School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;
2. Collaboration Innovation Center for Advanced Aero-Engine, Beijing 100191, China

摘要

摘要: 使用基于流固耦合算法的叶片反扭程序,考虑了非定常气动力对叶片变形的非线性作用,研究了叶片反扭对跨声速大涵道比风扇性能的影响.以冷态叶型为起点,先计算离心力作用下的叶片变形,在此基础上使用流固耦合程序获得非定常气动力作用下的变形.考察了3个转速下叶片的动态变形对大涵道比风扇气动性能的影响.结果表明:在跨声速工况下,叶片表面激波位置的变化对叶片反扭角有很大作用,在考察的转速范围内,堵塞点使用设计叶型计算的流量大于动态叶型下的流量,数值达7%,将导致发动机起飞推力小于预测值.结果表明在大涵道比风扇设计阶段,预测气动性能使用准确叶型的重要性.
- 叶轮机械 /
- 叶片反扭 /
- 大涵道比风扇 /
- 流固耦合 /
- 风扇性能
Abstract: Influence of blade untwist on transonic high bypass ratio fan performance were studied using the software based on the fluid-solid coupling algorithm, considering the nonlinear effects of unsteady aerodynamic force on the blade deformation. Firstly, the deformation induced by centrifugal force was calculated starting from the cold blade shape, and then the deformation induced by unsteady aerodynamic force was obtained using the fluid-solid coupling software. The effect of the dynamic blade deformation on aerodynamic performance of the high bypass ratio fan was investigated at three rotation speeds. Results show that changes of the shock position on the blade surface have significant influence on the blade untwist angle under the transonic conditions. In the rotation speed range concerned, the calculated mass flow rate by the designed blade shape is greater than that by the dynamic one up to 7%, which causes the engine takeoff thrust less than the predicted value. The results also indicate that the accurate blade shape is important for predicting aerodynamic performance during the design stage.
- turbomachinery /
- blade untwist /
- high bypass ratio fan /
- fluid-solid coupling /
- fan performance

HTML

参考文献(18)

[1]	陈懋章,刘宝杰.风扇/压气机气动设计技术发展趋势-用于大型客机的大涵道比涡扇发动机[J].航空动力学报,2008,23(6):961-975. CHEN Maozhang,LIU Baojie.Fan/compressor aero design trend and challenge on the development of high bypass ratio turbofan[J].Journal of Aerospace Power,2008,23(6):961-975.(in Chinese)
[2]	宋兆鸿,熊昌炳,郑光华.航空燃气涡轮发动机强度设计[M].北京:北京航空航天大学出版社,1988.
[3]	陈懋章,刘宝杰.大涵道比涡扇发动机风扇/压气机气动设计技术分析[J].航空学报,2008,29(3):513-526. CHEN Maozhang,LIU Baojie.Fan/compressor aero design technology for high bypass ratio turbofan[J].Acta Aeronautica et Astronautica Sinica,2008,29(3):513-526.(in Chinese)
[4]	Wilson M J,Imregun M,Sayma A I.The effect of stagger variability in gas turbine fan assemblies[J].Journal of Turbomachinery,2007,129(2):404-411.
[5]	Kallesøe B S,Hansen M H.Some effects of large blade deflections on aeroelastic stability[R].AIAA-2009-839,2009.
[6]	Roehle I,Le Guevel A,Fradin C.3D-shock visualisation in a transonic compressor rotor[J].Optics and Laser Technology,1999,31(1):67-73.
[7]	Yamamoto O,August R.Structural and aerodynamic analysis of a large-scale advanced propeller blade[J].Journal of Propulsion and Power,1992,8(2):367-373.
[8]	Kaza K R V,Mehmed O,Narayanan G V,et al.Analytical flutter investigation of a composite propfan model[R].AIAA 87-0738,1987.
[9]	Srivastava R,Sankar L N,Reddy T S R,et al.Application of an efficient hybrid scheme for aeroelastic analysis of advanced propellers[J].Journal of Propulsion and Power,1991,7(5):767-775.
[10]	廖伟丽,许斌,逯鹏,等.部分负荷下混流式水轮机转轮叶片变形对流场的影响[J].机械工程学报,2006,42(6):55-59. LIAO Weili,XU Bin,LU Peng,et al.Influence of runner blade deformation on fluid field of francis turbine under part load[J].Chinese Journal of Mechanical Engineering,2006,42(6):55-59.(in Chinese)
[11]	王宏亮,席光.离心叶轮几何形变对气动性能的影响[J].西安交通大学学报,2009,43(5):46-50. WANG Hongliang,XI Guang.Influence of centrifugal blade deformation on impeller aerodynamic performance[J].Journal of Xi'an Jiaotong University,2009,43(5):46-50.(in Chinese)
[12]	LIU Gaolian.The generalized untwist problem of rotating blades:a coupled aeroelastic formulation[J].International Journal of Turbo and Jet Engines,1995,12(2):109-117.
[13]	封卫兵,何吉欢,刘高联.大变形耦合热弹性动力学的变分原理[J].上海交通大学学报,2001,35(4):614-617. FENG Weibing,HE Jihuan,LIU Gaolian.Variational principles for coupled thermoelasticity with finite dispalcement[J].Journal of Shanghai Jiaotong University,2001,35(4):614-617.(in Chinese)
[14]	Sadeghi M,Liu F.Coupled fluid-structure simulation for turbomachinery blade rows[R].AIAA-2005-0018,2005.
[15]	郑赟.基于非结构网格的气动弹性数值方法研究[J].航空动力学报,2009,24(9):2069-2077. ZHENG Yun.Computational aeroelasticity with an unstructured grid method[J].Journal of Aerospace Power,2009,24(9):2069-2077.(in Chinese)
[16]	郑赟,田晓,杨慧.跨声速风扇叶片变形对气动性能的影响[J].航空动力学报,2011,26(7):1621-1627. ZHENG Yun,TIAN Xiao,YANG Hui.Impact of blade deflection on aerodynamic performance of a transonic fan[J].Journal of Aerospace Power,2011,26(7):1621-1627.(in Chinese)
[17]	郑赟,王彪,杨慧.跨声速风扇叶片的反扭设计研究[J].机械工程学报,2013,49(5):147-153. ZHENG Yun,WANG Biao,YANG Hui.Numerical study on blade unrunning design of a transonic fan[J].Journal of Mechanical Engineering,2013,49(5):147-153.(in Chinese)
[18]	郑赟,王彪,王静,等.多块协调变形的网格变形技术及其应用[J].航空计算技术,2012,42(1):83-87. ZHENG Yun,WANG Biao,WANG Jing,et al.Mesh deforming technique based on compatibility of multi-block structured mesh deformation and its application to blade aeroelastic analysis in turbomachinery[J].Aeronautical Computing Technique,2012,42(1):83-87.(in Chinese)