基于动叶污垢沉积的数值模拟

石慧; 陈绍文; 张辰; 王松涛; 王仲奇

基于动叶污垢沉积的数值模拟

哈尔滨工业大学能源科学与工程学院, 哈尔滨 150001

基金项目: 国家高技术研究发展计划(2008AA5A302); 中央高校基本科研业务费专项基金(HIT.NSRIF.2010033)

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出版历程
- 收稿日期: 2011-06-15
- 刊出日期: 2012-05-28

Numerical simulation of fouling deposition in compressor rotor

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

摘要

摘要: 采用三维数值方法研究了污垢沉积对压气机动叶性能的影响.对具有一定典型性的真实压气机动叶NASA Rotor 37进行数值研究,通过与文献中实验数据的对比,校核了商业CFD(computational fluid dynamics)计算代码的可靠性,结果表明计算得到的性能曲线与实验数据有较好的一致性,应用于数值模拟手段是可行的.随后通过增加叶片和端壁的表面粗糙度和厚度来模拟不同的污垢沉积程度对压气机动叶性能的影响,结果表明:增加叶片厚度和表面粗糙度都将引起总压比和等熵效率降低;增加表面粗糙度将导致流量下降,稳定工况范围向小流量方向移动;而增加叶片厚度将使得稳定工况范围明显减小,堵点流量下降较显著,这将导致动叶工作特性恶化程度增大.
- 航空发动机 /
- 压气机动叶 /
- 污垢沉积 /
- 表面粗糙度 /
- 厚度
Abstract: Three-dimensional numerical simulation to study the influence of fouling deposition on compressor rotors was carried out.As a representative of realistic compressor rotor,the NASA Rotor 37 was considered to perform a numerical investigation and by comparing with the experimental data available from literature,the reliability of commercial CFD(computational fluid dynamcics) computational code was validated.The results show that computed performance maps achieve a good agreement with the experimental data,so it’s practicable using the means of numerical simulations on the study.Then the influence of different fouling deposit degree on compressor rotor performance was simulated by adding surface roughness and thickness on the blade and end-wall.The results indicated that increasing surface roughness and thickness on the blade can make total pressure ratio and isentropic efficiency decrease,and increasing wall roughness can make flow reduce,rotor stable operating range transfer to small flow.Also,increasing blade thickness can make stable operating range decreased obviously,the flow reduced observably at the blockage point,which lead to increase on the deterioration degree of rotor performance.
- aircraft engine /
- compressor rotor /
- fouling deposition /
- roughness /
- thickness

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参考文献(12)

[1]	Suder K L,Chima R V,Strazisar A J,et al.The effect of adding roughness and thickness to a transonic axial compressor rotor[J].ASME Journal of Turbomachinery,1995,117(4):491-505.
[2]	Bammert K,Woelk G U.The influence of the blading surface roughness on the aerodynamic behavior and characteristic of an axial compressor.ASME Paper 79-GT-102,1979.
[3]	Syverud E,Brekke O,Bakken,L E.Axial compressor deterioration caused by saltwater ingestion.ASME Journal of Turbomachinery,2007,129(1):119-127.
[4]	Syverud E,Bakken L E.The impact of surface roughness on axial compressor performance deterioration.ASME Paper GT-2006-90004,2006.
[5]	Morini M,Pinelli M,Spina P R,et al.Computational fluid dynamics simulation of fouling on axial compressor stages[J].Journal of Engineering for Gas Turbines and Power,2010,132(7):072401(10 pages).
[6]	Gbadebo S A,Hynes T P,Cumpsty N A.Influence of surface roughness on three-dimensional separation in axial compressors[J].ASME Journal of Turbomachinery,2004,126(4):455-463.
[7]	侯乐毅,吴艳辉,楚武利.轴流压气机叶片加厚对气动性能影响分析[J].流体机械,2004,32(6):16-19. HOU Leyi,WU Yanhui,CHU Wuli.Numerical simulation on effects on increasing blade thickness on aerodynamic performance of axial compressor[J].Fluid Machinery,2004,32(6):16-19.(in Chinese)
[8]	李东,樊照远,张娟,等.压气机叶片粗糙度对其性能衰退的影响研究[J].航空发动机,2009,35(5):32-35. LI Dong,FAN Zhaoyuan,ZHANG Juan,et al.Influence of blade roughness on compressor performance deterioration[J].Aeroengine,2009,35(5):32-35.(in Chinese)
[9]	李本威,李冬,李姜华,等.单级压气机性能衰退定量研究[J].航空动力学报,2010,25(7):1588-1594. LI Benwei,LI Dong,LI Jianghua,et al.Quantitative research on performance degradation of single-stage compressor[J].Journal of Aerospace Power,2010,25(7):1588-1594.(in Chinese)
[10]	Reid L,Moore R D.Design and overall performance of four highly loaded,high-speed inlet stages for an advanced high- pressure-ratio core compressor.NASA-TP-1337,1978.
[11]	Reid L,Moore R D.Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26,respectively,and with design pressure ratio of 1.82.NASA-TP-1338,1978.
[12]	ANSYS Incorporated.ANSYS CFX-solver,release 10.0:theory[M]. :ANSYS Incorporated,2005.