转静干涉下压气机叶片尾缘锯齿设计与性能优化

doi:10.12382/bgxb.2023.0981

摘要/Abstract

摘要：

转静干涉效应诱发了压气机叶片尾流的复杂激扰行为,而尾缘锯齿特征为叶片尾流的激扰控制提供了有效手段。在考虑叶排间转静干涉的基础上,通过在静子叶片尾缘引入锯齿特征,以改善其对叶片尾流扰动以及压气机性能的影响,并进一步利用拉丁方试验设计优化了转子叶型,实现转静干涉下压气机叶片的尾流扰动控制与性能优化。研究结果表明:非均布锯齿特征有效改善了静子叶片的尾流形态,增强了叶片主流与尾流区域的混合效应,减小了叶片尾缘的速度亏损;跨声速压气机的效率提高了2.70%,稳定工作范围提高了12.31%;通过优化转子叶片型面,压气机效率提高至91.42%,进一步拓宽了其性能裕度;研究成果不仅对尾流扰动控制具有重要的理论价值,而且对高性能叶盘系统的设计具有重要的工程意义。

关键词: 压气机叶片, 尾缘锯齿, 尾流扰动, 工作性能, 优化设计

Abstract:

Complex excitation of compressor blade wakes is induced by the effect of rotor-stator interaction. The trailing-edge serrations are used as an effective means for controlling the excitation of blade wakes. Considering the interaction of rotor-stator blades, the serrations at stator trailing edge are designed to improve the wake turbulence of blades and the performance of compressor. Additionally, the experimental design of Latin square is applied to optimize the profile of rotor blades. This method is used to control the wake disturbance of compressor blades and optimize their performance under the effect of rotor-stator interaction. The results indicate that the wake patterns of stator blades are effectively improved by the distribution of non-homogeneous serrations, the mixing effects between blade mainstream and wake regions are enhanced, and the velocity loss at blade trailing edge is reduced. Consequently, the efficiency of transonic compressor is improved by 2.70%, and the stable operating range is increased by 12.31%. The efficiency of compressor is increased to 91.42% by optimizing the profile of rotor blade, and its performance margin is further expanded. This research not only has an important theoretical significance for the wake control, but also has a great engineering significance in the design of high-performance blade-disk system.

Key words: compressor blade, trailing-edge serration, wake disturbance, operating performance, optimization design

中图分类号:

V231.3

杨文军, 隋东东, 王旭鹏, 潘五九, 王磊. 转静干涉下压气机叶片尾缘锯齿设计与性能优化[J]. 兵工学报, 2024, 45(12): 4565-4577.

YANG Wenjun, SUI Dongdong, WANG Xupeng, PAN Wujiu, WANG Lei. Performance Optimization and Serrated Design of Trailing Edge on Compressor Blade under the Effect of Rotor-stator Interaction[J]. Acta Armamentarii, 2024, 45(12): 4565-4577.

图/表 29

图1 跨声速压气机模型及其计算域

Fig.1 Transonic compressor model and its computational domain

图2 有限元网格模型

Fig.2 The model of finite element mesh

图3 计算网格独立性验证

Fig.3 Independent validation of computational mesh

图4 压气机特性曲线对比

Fig.4 Comparison of compressor characteristic curves

表1 数值仿真与试验结果的偏差值对比

Table 1 Comparison of deviation values between numerically simulated and experimental results

工况点	参数	试验结果^[23]	仿真结果	偏差值/%
堵塞点	总压比	1.630	1.627	0.18
	效率	0.882	0.880	0.23
失速点	总压比	1.649	1.636	0.79
	效率	0.818	0.801	2.12

图5 沿叶高方向叶片流场的马赫数分布

Fig.5 Mach number distribution of blade flow field along the blade height

图6 S1流面示意图

Fig.6 Schematic diagram of S1 flow surface

图7 不同工况点转子叶片的马赫数分布

Fig.7 Mach number distribution of rotor blade at different working points

图8 鸟类羽翼尾缘锯齿结构

Fig.8 Serrated structure of bird wing

图9 尾缘锯齿参数定义

Fig.9 Definition of trailing-edge serration parameters

图10 锯齿结构的尾流特性

Fig.10 Wake flow characteristics of serrated structure

表2 3种不同锯齿叶片设计方案

Table 2 Three different serrated blade design schemes

模型	方案1	方案2	方案3
模型	h/λ_o系列	λ/c_o系列	λ/h_o系列
1	1.00	0.12	1.00
2	1.60	0.16	1.40
3	2.00	0.20	1.60

图11 叶片尾缘锯齿设计

Fig.11 The design of blade serrations at trailing edge

图12 在不同叶高区域锯齿叶片的尾流速度增长率对比

Fig.12 Growth rates of wake velocity at different serrated blade spans

图13 叶高与λ/co值的拟合

Fig.13 Fitting of blade spans and λ/co values

表3 锯齿尺寸与尾流速度的匹配设计

Table 3 Matching design based on serrated sizes and wake velocities

叶高/%	λ, h/mm	v_o/(m·s^-1)
8	12.02	177.54
16	11.67	173.82
23	11.18	168.47
31	10.71	163.13
39	10.12	156.14
47	9.80	152.20
54	9.23	144.88
62	8.54	135.40
70	8.17	129.98
77	7.84	124.92
85	7.55	120.26
93	7.17	113.81

图14 3种静子叶片

Fig.14 Three kinds of stator blades

图15 不同静子叶片压气机的特性曲线

Fig.15 Characteristic curves of compressor with different stator blades

表4 压气机稳定工作流量对比

Table 4 Comparison of compressor stable operating mass flows

静子叶片类型	堵塞流量/ (kg·s^-1)	失速流量/ (kg·s^-1)	流量范围/ (kg·s^-1)	增长率/%
原始	34.43308	30.9214	3.51194	0
均匀锯齿	34.52812	30.8007	3.72742	6.13
非均布锯齿	34.62448	30.6802	3.94428	12.31

图16 沿叶高方向不同静子叶片出口的马赫数分布

Fig.16 The distribution of Mach number at different stator outlets along the blade height

图17 优化设计流程

Fig.17 The process of optimization design

图18 转子叶片的几何参数化

Fig.18 Geometrical parameterization of rotor blade

表5 转子叶片前缘、尾缘安装角及其优化范围

Table 5 Mounting angle of rotor blade at leading edge and trailing edge and their optimized ranges

叶高/%	LE_n/(°)	TE_n/(°)	优化区间/(°)
0	-39.580	23.288	LE₁∈[-41,-37], TE₁∈[21,25]
25	-42.243	-13.081	LE₂∈[-44,-40], TE₂∈[-15,-11]
50	-52.358	-35.978	LE₃∈[-56,-50], TE₃∈[-37,-33]
75	-59.217	-49.87	LE₄∈[-62,-55], TE₄∈[-51,-47]
100	-65.328	-53.202	LE₅∈[-67,-63], TE₅∈[-58,-50]

表6 优化后转子叶片的前缘、尾缘安装角

Table 6 Mounting angle of the optimized rotor blade at

叶高/%	LE_n/(°)	TE_n/(°)
0	-39.659	21.099
25	-42.496	-12.113
50	-55.395	-36.770
75	-55.783	-50.169
100	-66.243	-57.778

图19 优化前后转子叶片的型面对比

Fig.19 Profiles of rotor blade before and after optimization

图20 优化前后转子叶片的尾流速度分布

Fig.20 Wake velocity distributions of rotor blade before and after optimization

图21 优化前后转子叶片沿弦长方向的压力分布

Fig.21 Pressure distributions of rotor blade along the length direction before and after optimization

图22 转静叶片优化设计后的压气机叶栅模型

Fig.22 The model of compressor cascade after optimization design of rotor-static blades

图23 转静叶片优化设计后压气机的特性曲线

Fig.23 Characteristic curves of compressor after optimization design of rotor-stator blades

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