典型高负荷大弯角压气机叶型的标准叶栅试验

doi:10.7527/S1000-6893.2024.31651

Abstract

Abstract:

Reliable and comprehensive compressor cascade test data are essential for establishing high-load compressor design systems and verifying the accuracy of numerical methods. In response to the demand for standard cascade test data of high-load compressor blade roots， the absence of authoritative test data of China， the inadequacy of publicly available data for high-load design needs， and the issue of data misuse due to the lack of flow field quality detection， the National Science and Technology Major Project Group conducted extensive research and discussions. With the support of the research results from Northwestern Polytechnical University on the influence mechanisms and regulation strategies of planar cascade wind tunnel flow field quality， the independently designed modern high-load compressor standard model cascade NPU-28 （with a blade camber angle of 43.5°， solidity of 1.72， and diffusion factor of 0.5） was established. This study obtained extensive experimental data， including cascade attack angle characteristics， isotropic Mach number on the blade surface， total pressure loss coefficient at the cascade channel exit， and exit flow angle for nine operating conditions within the inflow Mach number range of 0.4 and attack angle range of -10.9° to 5.1°. The data also provide flow field quality parameters， such as inflow Mach number uncertainty， axial velocity density ratio， and exit periodic index， along with measurement positions， test conditions， and inflow turbulence intensity， offering complete test information.

Key words: compressor cascade, linear cascade wind tunnel test, high-load, large turning angle, standard model of wind tunnel

CLC Number:

V231.3

Ruiyu LI, Ming CAI, Bo OUYANG, Limin GAO, Bo LIU, Baojie LIU. Standard cascade test for typical high-load and large turning angle compressor arfoils[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(16): 131651.

Figures/Tables 15

Fig.1

Table 1

Fig.2

Table 2

Fig.3

Fig. 4

Fig.5

Table 3

Periodicity indexes of NPU-28 cascade at outlet （without flow field control）

i/（°）	$P I M a 2$	$P I β 2$
-8.9	1.05	2.73
-2.9	0.66	3.10
3.1	2.71	4.20

Table 3

Fig.6

Fig.7

Table 4

Outflow periodicity index of NPU-28 cascade （AVDR=1.1）

i/（°）	$P I M a 2$	$P I β 2$
-10.9	0.71	1.25
-2.9	1.29	1.09
3.1	1.09	1.67

Table 4

Fig.8

Fig.9

Fig.10

Fig.11

References 24

[1]	凌代军，代秋林，朱榕川，等. 叶栅试验技术综述［J］. 实验流体力学， 2021， 35（3）： 30-38.
	LING D J， DAI Q L， ZHU R C， et al. Review of the cascade experimental technology［J］. Journal of Experiments in Fluid Mechanics， 2021， 35（3）： 30-38 （in Chinese）.
[2]	张庆典，马宏伟，杨益，等. 平面叶栅气动试验研究进展与展望［J］. 力学学报， 2022， 54（7）： 1755-1777.
	ZHANG Q D， MA H W， YANG Y， et al. Progress and prospect of aerodynamic experimental research on linear cascade［J］. Chinese Journal of Theoretical and Applied Mechanics， 2022， 54（7）： 1755-1777 （in Chinese）.
[3]	LIEBLEIN S. Aerodynamic design of axial-flow compressors. VI—Experimental flow in two-dimensional cascades： NACA-RM-E55K01a［R］. Washington， D.C.： NACA， 1955.
[4]	JOHNSON I A， Bullock R O. Aerodynamic design of axial-flow compressors： NASA-SP-36［R］. Washington， D.C.： NASA， 1965.
[5]	HOWELL A R. The present basis of axial flow compressor design： Part 1—Cascade theory and performance ARC-R&M-2095（6048）［R］. London： ARC， 1942.
[6]	HOWELL A R. Fluid dynamics of axial compressors［J］. Proceedings of the Institution of Mechanical Engineers， 1945， 153（1）： 441-452.
[7]	SCHREIBER H A， STARKEN H. Experimental cascade analysis of a transonic compressor rotor blade section［J］. Journal of Engineering for Gas Turbines Power.， 1984， 106（2）： 288-294.
[8]	STEINERT W， EISENBERG B， STARKEN H. Design and testing of a controlled diffusion airfoil cascade for industrial axial flow compressor application［J］. Journal of Turbomachinery， 1991， 113（4）： 583-590.
[9]	PANCHAL S， MAYAVANSHI V. Experimental study of flow through compressor cascade［J］. Case Studies in Thermal Engineering， 2017， 10： 234-243.
[10]	高宇，钟兢军，李晓东，等. 跨声速压气机动叶平面叶栅实验［J］. 航空动力学报， 2016， 31（5）： 1178-1185.
	GAO Y， ZHONG J J， LI X D， et al. Experiment on rotor plane cascade of transonic compressor［J］. Journal of Aerospace Power， 2016， 31（5）： 1178-1185 （in Chinese）.
[11]	兰发祥，周拜豪，梁德旺，等. 跨、超声速吸附式压气机平面叶栅试验［J］. 航空动力学报， 2010， 25（5）： 1123-1128.
	LAN F X， ZHOU B H， LIANG D W， et al. Experimental investigation of transonic and supersonic aspirated compressor cascades［J］. Journal of Aerospace Power， 2010， 25（5）： 1123-1128 （in Chinese）.
[12]	蔡明，高丽敏，李瑞宇，等. 亚声速压气机平面叶栅风洞标准模型建立［J］. 航空学报， 2025， 46（2）： 119-136.
	CAI M， GAO L M， LI R Y， et al. Establishment of standard model of linear cascade wind tunnel for subsonic compressor［J］. Acta Aeronautica et Astronautica Sinica， 2025， 46（2）： 119-136 （in Chinese）.
[13]	刘波，周新海，严汝群. 轴流压气机可控扩散叶型的数值优化设计［J］. 航空动力学报， 1991， 6（1）： 9-12.
	LIU B， ZHOU X H， YAN R Q. Numerical optimization program for designing controlled diffusion compressor blading［J］. Journal of Aerospace Power， 1991， 6（1）： 9-12 （in Chinese）.
[14]	魏巍，刘波，杜炜，等. 可控扩散叶型与双圆弧叶型实验对比研究［J］. 推进技术， 2017， 38（1）： 61-68.
	WEI W， LIU B， DU W， et al. Experimental comparison of controlled diffusion airfoils with double circle airfoils［J］. Journal of Propulsion Technology， 2017， 38（1）： 61-68 （in Chinese）.
[15]	HERRIG L J， EMERY J C， ERWIN J R. Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds： NACA-RM-L51G31［R］. Washington， D.C.： NACA， 1957.
[16]	ANDREWS S J. Tests related to the effect of profile shape and camber-line on compressor cascade performance： ARC-R&M-2743［R］. London： ARC， 1965.
[17]	蔡明，高丽敏，刘哲，等. 基于抽吸的亚声速平面叶栅风洞流场品质控制研究［J］. 推进技术， 2021， 42（9）： 1985-1992.
	CAI M， GAO L M， LIU Z， et al. Flow field quality control of subsonic linear cascade wind tunnel based on suction［J］. Journal of Propulsion Technology， 2021， 42（9）： 1985-1992 （in Chinese）.
[18]	蔡明，高丽敏，刘哲，等. 不同条件下平面叶栅风洞流场品质的实验研究［J］. 推进技术， 2021， 42（5）： 1162-1170.
	CAI M， GAO L M， LIU Z， et al. Experimental study on flow field quality of linear cascade wind tunnel under different conditions［J］. Journal of Propulsion Technology， 2021， 42（5）： 1162-1170 （in Chinese）.
[19]	蔡明，高丽敏，晋文浩，等. 平面叶栅风洞流场品质的被动调控策略［J］. 航空动力学报， 2024， 39（7）： 222-233.
	CAI M， GAO L M， JIN W H， et al. Passive control strategy for flow quality of linear cascade wind tunnel［J］. Journal of Aerospace Power， 2024， 39（7）： 222-233 （in Chinese）.
[20]	蔡明，王利敏，高丽敏，等. 高负荷平面叶栅风洞流场品质分析及改进试验［J］. 空气动力学学报， 2025， 43（1）：44-52.
	CAI M， WANG L M， GAO L M， et al. Analysis and im-provement of flow field quality in high-load linear cas-cade wind tunnel［J］. Acta Aerodynamica Sinica， 2025，43（1）： 44-52 （in Chinese）.
[21]	高丽敏，蔡宇桐，曾瑞慧，等. 叶片加工误差对压气机叶栅气动性能的影响［J］. 推进技术， 2017， 38（3）： 525-531.
	GAO L M， CAI Y T， ZENG R H， et al. Effects of blade machining error on compressor cascade aerodynamic performance［J］. Journal of Propulsion Technology， 2017， 38（3）： 525-531 （in Chinese）.
[22]	蔡明，高丽敏，刘哲，等. 高负荷扩压平面叶栅进口均匀性分析及改进［J］. 工程热物理学报， 2021， 42（12）： 3164-3169.
	CAI M， GAO L M， LIU Z， et al. Analysis and modification on inflow uniformity of highly-loaded compressor linear cascade［J］. Journal of Engineering Thermophysics， 2021， 42（12）： 3164-3169 （in Chinese）.
[23]	高丽敏，刘哲，蔡明，等. 高负荷扩压叶栅吹风试验流场二维性控制技术研究［J］. 实验流体力学， 2021， 35（2）： 13-21.
	GAO L M， LIU Z， CAI M， et al. Study on two-dimensional control technology of flow field in high-load compressor cascade test［J］. Journal of Experiments in Fluid Mechanics， 2021， 35（2）： 13-21 （in Chinese）.
[24]	高丽敏，刘哲，蔡明，等. 四种风洞收缩段流场特性对比［J］. 航空动力学报， 2020， 35（8）： 1695-1705.
	GAO L M， LIU Z， CAI M， et al. Comparison on flow field characteristics of four wind tunnel contraction sections［J］. Journal of Aerospace Power， 2020， 35（8）： 1695-1705 （in Chinese）.

参数	设计值
扩散因子D	0.5
稠度τ	1.72
安装角γ/（°）	15.8
进气角β₁/（°）	44
出气角β₂/（°）	0.5
几何进气角β_1κ/（°）	46.9
几何出气角β_2κ/（°）	-2.1

编号	x_c /c	编号	x_c /c
1	0.077	6	0.462
2	0.154	7	0.538
3	0.231	8	0.615
4	0.308	9	0.692
5	0.385	10	0.769

Standard cascade test for typical high-load and large turning angle compressor arfoils

RichHTML

PDF (PC)

Knowledge

Abstract

Cite this article

share this article

Figures/Tables 15

References 24

Related Articles 8

Recommended Articles

Metrics

Comments

[1]	Ming CAI, Limin GAO, Ruiyu LI, Bo OUYANG, Bo LIU. Establishment of standard model of linear cascade wind tunnel for subsonic compressor [J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(2): 130547-130547.
[2]	Bo WANG, Yanhui WU, Lingju HUANG, Zixu WANG. Corner separation control in compressor cascade based on L-shaped endwall groove [J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(10): 129206-129206.
[3]	Tantao LIU, Ruiyu LI, Limin GAO, Lei ZHAO. Experimental data driven cascade flow field prediction based on data assimilation [J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628201-628201.
[4]	WANG Bo, WU Yanhui. Vortex-dynamics mechanism of tip-region unsteady flow in compressor cascade [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2020, 41(11): 123881-123881.
[5]	TIAN Simeng, WU Yun, ZHANG Haideng, LI Yinghong, LI Jun. Energy loss in a low-speed compressor cascade with dissipation function [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015, 36(10): 3249-3262.
[6]	ZHANG Haideng, WU Yun, LI Yinghong, ZHAO Qin. Investigation of Vortex Structure and Flow Loss in a High-speed Compressor Cascade [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(9): 2438-2450.
[7]	YANG Yanli, YANG Ailing, DONG Rui, CHEN Eryun, DAI Ren. Influence of Stagger Angle on Aerodynamic Sound Performance of Compressor Cascade [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, (4): 588-596.
[8]	Tao Deping;Ma Jihua. EXPERIMENTAL STUDY AND THEORETICAL ANAIYSIS OF SECONDARY FLOW IN A COMPRESSOR CASCADE [J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 1989, 10(3): 119-125.