Analysis and improvement of flow field quality in high-load planar cascade wind tunnel

CAI Ming; WANG Limin; GAO Limin; JING Lina; WANG Lei

doi:10.7638/kqdlxxb-2023.0214

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Analysis and improvement of flow field quality in high-load planar cascade wind tunnel

更新时间：2026-05-28

- Analysis and improvement of flow field quality in high-load planar cascade wind tunnel
- Vol. 43, Issue 1, Pages: 44-52(2025)
- 作者机构：
  
  1. 航空工业第一飞机设计研究院,西安,710089
  2. 西北工业大学动力与能源学院,西安,710072
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0214
  CLC： V211.3
- Published：2025
- 稿件说明：
移动端阅览
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 Ming, WANG Limin, GAO Limin, et al. Analysis and improvement of flow field quality in high-load planar cascade wind tunnel[J]. 2025, 43(1): 44-52.
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. DOI： 10.7638/kqdlxxb-2023.0214

CAI Ming, WANG Limin, GAO Limin, et al. Analysis and improvement of flow field quality in high-load planar cascade wind tunnel[J]. 2025, 43(1): 44-52. DOI： 10.7638/kqdlxxb-2023.0214.

摘要

良好的平面叶栅风洞流场品质是保证叶栅试验数据有效性的关键。详细测量并分析了某亚声速压气机平面叶栅在不同来流条件下的流场品质，根据叶栅风洞情况建立了相应的上端壁抽吸调控方案，研究了不同抽吸强度下上端壁抽吸对叶栅流场品质的改善效果。研究表明：高负荷压气机叶栅在整个工作范围均存在栅前流场不均匀、来流攻角不准确的问题，叶栅被测通道的实际攻角比风洞几何设定值大2°～3°。随着叶栅负荷增大（来流马赫数和攻角增加），流场品质逐渐下降；来流攻角同时影响着栅前马赫数和气流角的均匀性，来流马赫数主要影响栅前马赫数的均匀性。上端壁抽吸能够有效改善大攻角下叶栅流场品质不佳的问题，存在使叶栅流场品质达到最佳的临界抽吸静压，超过临界值后叶栅流场品质逐渐下降。临界抽吸静压下，栅前流场均匀性良好，被测通道的攻角与设定值的差异减小至0.5°～0.9°；叶栅二维性和出口总压损失周期性均有所提升，但是叶栅出气角周期性基本不变。

Abstract

High-quality flow fields in cascade wind tunnels are crucial to evaluate the aerodynamic performance of compressor cascades. This study examines the impact of different inflow conditions on the flow field quality in a planar cascade wind tunnel

utilizing a high-load compressor cascade. A suction scheme tailored to the wind tunnel’s upper end-wall is developed

and its effects on the flow field quality is investigated. The results indicate that the inflow inhomogeneity and inaccuracy of incidence angle persist across the cascade’s operational range. Notably

the measured incidence angles of the cascade passage exceed the assigned values by 2°～3°. The flow field quality deteriorates with increasing cascade load (increasing inlet Mach number and incidence angle). The incidence angle affects the inhomogeneity of the inlet Mach number and flow angle

while the inlet Mach number primarily affects the former. The upper end-wall suction can effectively improve the flow field quality at high incidence angles with appropriate suction pressure amplitudes. Under the critical suction pressure that yields the optimal flow field quality

the upstream flow field homogeneity is restored

and the difference between the measured and assigned incidence angles is reduced to 0.5°～0.9°. Both the two-dimensionality and the periodicity of the total pressure loss of the cascade are improved

but the periodicity of the outlet flow angle of the cascade remains essentially unchanged. This research provides valuable insights into improving flow field quality in cascade wind tunnels

particularly under high-load conditions.

关键词

Keywords

references

GOSTELOW J P. Cascade aerodynamics[M]. Oxford: Pergamon Press, 1984.

HERRIG L J, EMERY J C, ERWIN J R. Systematic two-dimensional cascade tests of NACA 65-series compressor blades at low speeds: NACA-TR-1368[R]. 1951.

POLLARD D, GOSTELOW J P . Some experiments at low speed on compressor cascades[J ] . Journal of Engineering for Power, 1967 , 89 ( 3 ): 427 − 436 .

JIANG Z L, LIN D J, YU H J , et al. Method of supersonic and transonic plane cascade test: HB 20145-2014[S]. Beijing: State Administration of Science, Technology and Industry for National Defense, 2015: 114(in Chinese).

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).

DUNAVANT J C, EMERY J C. Two-dimensional cascade investigation at Mach numbers up to 1.0 of NACA 65-series blade sections at conditions typical of compressor tips: NACA RM L58A02[R]. 1958.

HERGT A, MEYER R, ENGEL K. Experimental investigation of flow control in compressor cascades[C]// Proceedings of ASME Turbo Expo 2006: Power for Land, Sea, and Air, Barcelona, Spain. 2008: 231240.

KIESNER M, KING R. Multivariable closed-loop active flow control of a compressor stator cascade[J]. AIAA Journal, 2017, 55(10): 33713380.

Pianko M. Modern methods of testing rotating components of turbomachines: AGARD-AG-167[R]. 1972.

LEPICOVSKY J, MCFARLAND E R, CHIMA R V, et al. On flowfield periodicity in the NASA transonic flutter cascade: Part I: experimental study[C]//Proceedings of ASME Turbo Expo 2000: Power for Land, Sea, and Air, Munich, Germany, 2014.

SONG B, NG W. Influence of axial velocity density ratio in cascade testing of supercritical compressor blades[C]//Proc of the Proceedings of the 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Fort Lauderdale, Florida. Reston, Virigina: AIAA, 2004: AIAA2004-3414.

TIAN S M, PETRIE-REPAR P, GLODIC N, et al. CFD-aided design of a transonic aeroelastic compressor rig[J]. Journal of Turbomachinery, 2019, 141(10): 101003.

YANG Y, XU K J, LI S S, et al . Numerical simulation on flow periodic characteristics of linear cascade[J ] . Chinese Hydraulics Pneumatics, 2018 ( 9 ): 92 − 97 (in Chinese).

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).

CAI M, GAO L M, LIU Z, et al . Study on 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).

SUN P, ZHANG Y Z, FU W G, et al . Flow field quality improvement of transonic linear cascade test device[J ] . Journal of Propulsion Technology, 2022 , 43 ( 12 ): 210731 (in Chinese).

FU W G, YANG Z, ZHANG Y Z, et al . Numerical study on flow field quality improvement in a highly loaded linear cascade wind tunnel[J ] . Journal of Propulsion Technology, 2023 , 44 ( 7 ): 164 − 175 (in Chinese).

CAI Ming, GAO Limin, JIN Wenhao, et al. Passive control strategy for flow quality of linear cascade wind tunnel[J]. Journal of Aerospace Power, 2024, 39(7): 20220482(in Chinese).

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).

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