高压压气机出口级叶型加工偏差特征及其影响

刘佳鑫; 于贤君; 孟德君; 史文斌; 刘宝杰

doi:10.7527/S1000-6893.2020.23796

航空学报 >

2021 , Vol. 42 >Issue 2: 423796 - 423796

DOI: https://doi.org/10.7527/S1000-6893.2020.23796

材料工程与机械制造

高压压气机出口级叶型加工偏差特征及其影响

刘佳鑫 ,
于贤君 ,
孟德君 ,
史文斌 ,
刘宝杰

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1. 北京航空航天大学能源与动力工程学院, 北京 100083;
2. 北京航空航天大学航空发动机研究院, 北京 100083;
3. 中国航发沈阳发动机研究所, 沈阳 110015

收稿日期: 2020-01-04

修回日期: 2020-02-13

网络出版日期: 2020-04-20

基金资助

国家自然科学基金（51476004）；国家科技重大专项（2017-II-0001-0013）

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State and effect of manufacture deviations of compressor blade in high-pressure compressor outlet stage

LIU Jiaxin ,
YU Xianjun ,
MENG Dejun ,
SHI Wenbin ,
LIU Baojie

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1. School of Energy and Power Engineering, Beihang University, Beijing 100083, China;
2. Research Institute of Aeroengine, Beihang University, Beijing 100083, China;
3. AVIC Shenyang Engine Design Institute, Shenyang 110015, China

Received date: 2020-01-04

Revised date: 2020-02-13

Online published: 2020-04-20

Supported by

National Natural Science Foundation of China (51476004); National Science and Technology Major Project (2017-II-0001-0013)

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摘要

以高压压气机出口级叶片叶中截面作为研究对象，获得了实际压气机叶片加工偏差的分布特征，并分析了实际加工偏差对叶型气动性能的影响。以此为基础，研究了加工偏差对叶型性能的影响机理。研究结果表明，实际叶型加工偏差存在一定的系统性偏差，从而导致实际叶型气动性能的平均值偏离设计值。叶型偏差对叶型气动性能的影响存在一定的非线性效应，这在前缘区域更为明显，从而导致了平均叶型的气动性能与实际叶型平均性能出现了明显偏差。前缘附近的几何偏差对吸力面和压力面的速度峰值有较大的影响，因此前缘附近的偏差是使叶型的气动性能产生系统性偏差和增大不确定度的主要因素。根据对流动机理的分析，进口几何角偏差是导致叶型性能出现系统性偏差的主要原因；可以近似用均匀偏差来估计叶身加工偏差对正负攻角范围和损失的影响。

关键词： 加工偏差; 压气机叶片; 气动性能; 不确定度; 流动机理

本文引用格式

刘佳鑫 , 于贤君 , 孟德君 , 史文斌 , 刘宝杰 . 高压压气机出口级叶型加工偏差特征及其影响[J]. 航空学报, 2021 , 42(2) : 423796 -423796 . DOI: 10.7527/S1000-6893.2020.23796

Abstract

A mid-section blade of the high-pressure compressor outlet stage is studied to obtain the distribution characteristics of actual manufacture deviations and to analyze the effect of manufacture deviations on the aerodynamic performance of blades. The fluid mechanism of manufacture deviations on blade performance is also examined. Results show that the actual manufacture deviations have certain systematic deviations, leading to the variations of the average aerodynamic performance of the actual blades from the design value. Blade manufacture deviations have certain nonlinear effects on the blade performance, which is more noticeable on the blade leading edge. This results in a distinct disparity between the aerodynamic performance of the mean airfoil of the manufactured blades and the mean performance of all the manufactured blades. The geometric deviations near the leading edge has a considerable effect on the velocity spike of the suction and the pressure surface; therefore, these deviations have been the main factor causing systematic variations and increasing the uncertainty of the blade aerodynamic performance. According to the fluid mechanism, the inlet geometric angle deviations are the main cause of the systematic variations of the blade aerodynamic performance, and the effect of the body deviations on the positive/negative incidence range and losses can be estimated by uniform deviations.

Key words： manufacture deviations; compressor blades; aerodynamic performance; uncertainty; flow mechanism

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