Performance Optimization and Serrated Design of Trailing Edge on Compressor Blade under the Effect of Rotor-stator Interaction

doi:10.12382/bgxb.2023.0981

Abstract

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

CLC Number:

V231.3

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.

Figures/Tables 29

Fig.1 Transonic compressor model and its computational domain

Fig.2 The model of finite element mesh

Fig.3 Independent validation of computational mesh

Fig.4 Comparison of compressor characteristic curves

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

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

Fig.6 Schematic diagram of S1 flow surface

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

Fig.8 Serrated structure of bird wing

Fig.9 Definition of trailing-edge serration parameters

Fig.10 Wake flow characteristics of serrated structure

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

Fig.11 The design of blade serrations at trailing edge

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

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

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

Fig.14 Three kinds of stator blades

Fig.15 Characteristic curves of compressor with different stator blades

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

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

Fig.17 The process of optimization design

Fig.18 Geometrical parameterization of rotor blade

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]

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

Fig.19 Profiles of rotor blade before and after optimization

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

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

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

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

References 24

[1]	肖志祥, 崔文瑶, 刘健, 等. 新一代战斗机非定常流动数值研究综述[J]. 航空学报, 2020, 41(6): 64-79.
	XIAO Z X, CUI W Y, LIU J, et al. Review of numerical research on unsteady flows of the new generation fighters[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(6): 64-79. (in Chinese)
[2]	李博, 王兆祺, 兰发祥, 等. 三维叶片设计技术在现代压气机中的应用[J]. 航空动力, 2023, 3:60-62.
	LI B, WANG Z Q, LAN F X, et al. Three-dimensional blading technology for high performance compressor[J]. Aerospace Power, 2023, 3: 60-62. (in Chinese)
[3]	FU W G, SUN P. Effect of three non-axisymmetric stator schemes on compressor performance with distorted inlet[J]. Part G: Journal of Aerospace Engineering, 2022, 236(10): 2044-2056.
[4]	马宇晨, 吴东润, 吴俣, 等. 压气机环形叶栅尾迹特性试验与数值模拟研究[J]. 工程热物理学报, 2021, 42(10): 2536-2543.
	MA Y C, WU D R, WU Y, et al. Experimental and numerical investigation of the wake characteristics in an annular compressor cascade[J]. Journal of Engineering Thermophysics, 2021, 42(10): 2536-2543. (in Chinese)
[5]	ZHAO J Y, LU Q F, YANG D G. Experimental and numerical analysis of rotor-rotor interaction characteristics inside a multistage transonic axial compressor[J]. Energies, 2022, 15(7): 2627-2627.
[6]	魏巍, 任思源, 马护生, 等. 亚声速压气机平面叶栅雷诺数影响试验[J]. 航空动力学报, 2022, 37(5): 1020-1029.
	WEI W, REN S Y, MA H S, et al. Experiment of Reynolds number effects on subsonic compressor plane cascade[J]. Journal of Aerospace Power, 2022, 37(5): 1020-1029. (in Chinese)
[16]	YANG C H, FENG H Y, PENG Y H. Effects of trailing edge serrations on rotor/stator interaction noise in low-pressure turbines[J]. Journal of Propulsion Technology, 2022, 43(5): 132-141. (in Chinese)
[17]	LEE S, AYTON L, BERTAGNOLIO F, et al. Turbulent boundary layer trailing-edge noise: theory, computation, experiment, and application[J]. Progress in Aerospace Sciences, 2021, 126: 100737.
[18]	YE X M, ZHENG N, HU J M, et al. Numerical investigation of the benefits of serrated Gurney flaps on an axial flow fan[J]. Energy, 2022, 252: 1240772.
[19]	沈彦佑, 贾民平, 朱林. 基于拉丁超立方抽样的离心式吸叶机噪声分析与降噪优化研究[J]. 振动与冲击, 2016, 35(15): 93-97.
	SHEN Y Y, JIA M P, ZHU L. Noise analysis of centrifugal leaf vacuum based on Latin hypercube sampling[J]. Journal of Vibration and Shock, 2016, 35(15): 93-97. (in Chinese)
[20]	冯路宁, 程邦勤, 王加乐, 等. 整体涡旋流对跨声速压气机Stage 67影响的定常数值仿真研究[J]. 推进技术, 2021, 42(9): 1993-2001.
	FENG L N, CHENG B Q, WANG L J, et al. Steady numerical simulation of transonic compressor Stage 67 with bulk swirl distortion[J]. Journal of Propulsion Technology, 2021, 42(9):1993-2001. (in Chinese)
[21]	冯路宁, 程邦勤, 王加乐. 对涡旋流对跨声速压气机转子Rotor 67的影响[J]. 工程热物理学报, 2021, 42(9): 2284-2291.
	FENG L N, CHENG B Q, WANG L J. Effects of paired swirl distortion on Rotor 67 transonic compressor[J]. Journal of Engineering Thermophysics, 2021, 42(9): 2284-2291. (in Chinese)
[22]	LI N, LIU Y Q, LI L, et al. Numerical simulation of wind turbine wake based on extendedk-epsilon turbulence model coupling with actuator disc considering nacelle and tower[J]. IET Renewable Power Generation, 2021, 14(1): 3834-3842.
[7]	佟鼎, 田红艳, 刘欣源, 等. 进气弯管对离心压气机特性影响及弯管结构优化[J]. 兵工学报, 2021, 42(4):706-714.
	TONG D, TIAN H Y, LIU X Y, et al. Effect of inlet bend pipe on the centrifugal compressor performance and its optimization design[J]. Acta Armamentarii, 2021, 42(4): 706-714. (in Chinese) doi: 10.3969/j.issn.1000-1093.2021.04.004
[8]	JIANG C, HU J, WANG J Y, et al. Numerical investigation on short length-scale disturbance generation in an eccentric axial compressor rotor at a stable condition[J]. Aerospace Science and Technology, 2021, 109: 106439.
[9]	SHI L, MA H W, YU X H. POD analysis of the unsteady behavior of blade wake under the influence of laminar separation vortex shedding in a compressor cascade[J]. Aerospace Science and Technology, 2020, 105: 106056.
[10]	LI H F, ZHENG Q, JIANG B. Influence of rotor-stator axial clearance on compressor rotating stall characteristics[J]. Aerospace Science and Technology, 2023, 139: 108373.
[11]	胡义, 韩吉昂, 钱薪伟, 等. 不同造型方法下鼓包参数对跨声速压气机叶栅性能的影响[J]. 大连海事大学学报, 2021, 47(2):83-96.
	HU Y, HAN J A, QIAN X W, et al. Influence of bump parameters on the performance of a transonic compressor cascade under different bump configuration method[J]. Journal of Dalian Maritime University, 2021, 47(2): 83-96. (in Chinese)
[12]	王宪磊, 刘欣源, 张强, 等. 叶片前缘前掠对离心压气机性能的影响[J]. 车用发动机, 2023, 4: 21-28.
	WANG X L, LIU X Y, ZHANG Q, et al. Influence of blade leading edge sweep on centrifugal compressor performance[J]. Vehicle Engine, 2023, 4: 21-28. (in Chinese)
[13]	SONG Z Y, ZHENG X Q, WANG B T, et al. Aerodynamic and structural multidisciplinary optimization design method of fan rotors based on blade curvature constraints[J]. Aerospace Science and Technology, 2023, 136: 108187.
[14]	周创鑫, 成金鑫, 黄松, 等. 基于贝塞尔曲面参数化方法的1.5级高负荷轴流压气机气动优化[J]. 航空动力学报, 2021, 36(4): 673-686.
	ZHOU C X, CHENG J X, HUANG S, et al. Aerodynamic optimization of 1.5-stage highly loaded axial compressor through Bezier surface parameterization method[J]. Journal of Aerospace Power, 2021, 36(4): 673-686. (in Chinese)
[15]	邹如萍, 李传鹏, 安志强, 等. 锯齿尾缘叶片气动特性数值模拟研究[J]. 南京航空航天大学学报, 2021, 53(4): 546-550.
	ZOU R P, LI C P, AN Z Q, et al. Numerical simulation research on aerodynamic characteristics of sawtooth trailing edge blade[J]. Journal of Nanjing University of Aeronautics and Astronautics, 2021, 53(4): 546-550. (in Chinese)
[16]	杨成浩, 冯和英, 彭叶辉. 尾缘锯齿结构对低压涡轮动静干涉噪声的影响[J]. 推进技术, 2022, 43(5): 132-141.
[23]	HATHAWAY M D. Unsteady flows in a single-stage transonic axial-flow fan stator row: NASA-TM-88929[R]. Cleveland, OH, US: NASA Lewis Research Center, 1987.
[24]	OLADUGBA V A, BABATUNDE T O, ADELEKE L M. Relative efficiency of Latin square design to randomized designs[J]. International Journal of Mathematics and Statistics, 2022, 23(2): 31-40.