波纹对高亚声叶型性能影响试验与机理分析

杨光; 高丽敏; 王浩浩; 黄萍

doi:10.13224/j.cnki.jasp.20220480

波纹对高亚声叶型性能影响试验与机理分析

doi: 10.13224/j.cnki.jasp.20220480

杨光^{1, 2,},
高丽敏^{1, 2},
王浩浩^{1, 2},
黄萍³

1.
西北工业大学动力与能源学院，西安 710072
2.
西北工业大学翼型、叶栅空气动力学国家级重点实验室，西安 710072
3.
中国航发四川燃气涡轮研究院，四川绵阳 621000

基金项目: 国家自然科学基金（51790512）；自然科学基金面上项目（52175436）

详细信息

作者简介:
杨光（1995-），男，博士生，主要从事叶轮机械气动热力学研究

中图分类号: V231.1
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- 文章访问数: 28
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- 被引次数: 0
出版历程
- 收稿日期: 2022-07-04
- 网络出版日期: 2023-10-24

Experiment and mechanism analysis on the effect of waves on the performance of high-subsonic profile

YANG Guang^{1, 2
,},
GAO Limin^{1, 2},
WANG Haohao^{1, 2},
HUANG Ping³

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
The National Key Laboratory of Aerodymamic Design and Rescarch， Northwestern Polytechnical University，Xi’an 710072，China
3.
Sichuan Gas Turbine Establishment， Aero Engine Corporation of China，Mianyang Sichuan 621000，China

摘要

摘要:
基于压气机叶片加工过程中出现的波纹现象，加工出4种波纹形式叶栅试验件并开展平面叶栅吹风试验，得到波纹对叶型性能及表面负荷的影响规律并进行机理分析。结果表明：叶背波纹现象整体上增加叶型损失。负攻角下，叶背波纹对流场的影响会传播至叶背下游和叶盆，整体改变叶型表面压力分布。气流在波纹出现位置产生“加速-减速”的周期性更迭，波纹宽度直接决定了更迭的频次，不同的波纹初始相位影响叶背前缘区域加速趋势。叶背波纹会改变前缘“吸力峰”强度，波纹对叶型前缘转捩位置的作用机制与叶型自身特性有关，当波纹起始位置在原始叶型转捩位置前，吸力峰强度的变化会改变前缘转捩位置。
- 压气机 /
- 波纹度 /
- 平面叶栅试验 /
- 气动性能 /
- 前缘转捩
Abstract:
Based on the appearance of waves in the compressor blade processing, cascades with four kinds of waves were processed, and the plane cascade experiment was carried out, then the influences of aerodynamic performance and pressure distribution were obtained and the mechanism was analyzed. Results showed that the loss of those profiles with waves was overall larger than that of original profile. Under negative attack of angle, the influence of wave spread to the downstream and pressure side and changed the pressure distribution of profile. Moreover, the flow experienced repeated acceleration-deceleration changes on suction side of the blade where waves appeared. The width of the wave directly determined the frequency of acceleration-deceleration changes, and different initial phases of waves affected the acceleration circumstances of leading edge. The wave on suction side could change the “spike” close to the leading edge, the action mechanism for waves changing transition position was related to the characteristics of the airfoil itself; when waves occurred before the location of transition, the variation of “spike” could change the location of transition.
- compressor /
- waviness /
- plane cascade experiment /
- aerodynamic performance /
- leading edge transition

HTML

图 1 波纹简化模型

Figure 1. Simplified model of waves

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图 2 4种叶栅试验件叶型对比

Figure 2. Comparison of profiles of four types of cascade

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图 3 静压孔相对位置

Figure 3. Relative position of static pressure holes

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图 4 Plan1叶栅试验件

Figure 4. Plan1 cascade

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图 5 风洞结构

Figure 5. Wind tunnel structure

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图 6 流场周期性检查（Plan0, i=2°）

Figure 6. Periodic check of the flow （Plan0, i=2°）

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图 7 叶栅试验得到的攻角特性曲线

Figure 7. Angle of attack characteristic curves obtained from cascade experiment

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图 8 等熵马赫数分布（Ma=0.7）

Figure 8. Isentropic Mach number distribution （Ma=0.7）

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图 9 等熵马赫数分布（Ma=0.8）

Figure 9. Isentropic Mach number distribution （Ma=0.8）

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图 10 y⁺值云图

Figure 10. Contour of y⁺ value

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图 11 数值结果与试验结果对比（Ma=0.7，i=−2°）

Figure 11. Comparison of numerical results with experimental results （ Ma=0.7，i=−2°）

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图 12 叶片表面等熵马赫数曲线

Figure 12. Isentropic Mach number curves of blade surface

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图 13 间歇因子云图（Ma=0.7, i=5°）

Figure 13. Contour of intermittent （Ma=0.7, i=5°）

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图 14 间歇因子云图（Ma=0.8, i=5°）

Figure 14. Contour of intermittent （Ma=0.8, i=5° ）

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表 1 原始叶型参数

Table 1. Original profile parameters

参数	数值
进口几何构造角/（°）	49
出口几何构造角/（°）	7.2980
安装角/（°）	28.4594
最大相对厚度D_max/C	0.0800
最大相对厚度位置x_max/C	0.4800
弦长C/mm	71.1760
栅距T/mm	35.7660

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表 2 4种简化波纹模型参数

Table 2. Parameters of four simplified waves

方案	Z/mm	W/mm	${\varphi} $/rad
Plan0	0		0
Plan1	0.15	33	0
Plan2	0.15	33	${\text{π}}$
Plan3	0.15	11	0

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表 3 试验工况

Table 3. Work conditions

攻角i/（°）	−2	0	2	3	5	7
周期性检查			Plan0, 1, 2, 3
Ma=0.7	Plan0, 1, 2, 3	Plan0, 1, 2, 3	Plan0, 1, 2, 3	Plan0, 1, 2, 3	Plan0, 1, 2, 3	Plan0, 1, 2, 3
Ma=0.8	Plan0,1,3	Plan0, 1, 2, 3	Plan0, 1, 2, 3	Plan0, 1, 2, 3	Plan0, 1, 2, 3	Plan0, 1, 2, 3

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