Design and actualization of the variable density plane cascade wind tunnel

WEI Wei; MA Husheng; ZHOU Xiaogang; WU Junqiang; PENG Qiang; REN Zebin

doi:10.11729/syltlx20210175

Volume 36 Issue 5

Sep. 2022

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Journal of Experiments in Fluid Mechanics > 2022 > 36(5): 24-33. > DOI: 10.11729/syltlx20210175

WEI W，MA H S，ZHOU X G，et al. Design and actualization of the variable density plane cascade wind tunnel[J]. Journal of Experiments in Fluid Mechanics, 2022，36（5）：24-33.. DOI: 10.11729/syltlx20210175

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Design and actualization of the variable density plane cascade wind tunnel

1.
Aerospace Technology Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China
2.
High Speed Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China
3.
China Aerodynamics Research and Development Center, Mianyang　621000, China
4.
Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang　621000, China

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Received Date: December 29, 2021
Revised Date: March 26, 2022
Accepted Date: April 05, 2022

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Abstract

Abstract

In order to meet the need of the variable Reynolds number plane cascade tests for the advanced turbofan engine, the variable density plane cascade wind tunnel was designed to change the subsonic, transonic and supersonic flow efficiently, adjust the Mach number （Ma） and Reynolds number （Re） independently, combine the compressor and turbine cascade tests and possess the ability of heat transfer or cooling experiments. The general design project of the wind tunnel was put forward, and the ejector, the flexible nozzle as well as the test chamber design problems were introduced in details. The results of the flow field debugging and the typical cascade tests were analysed. The research reveals that the design technologies of the components satisfy the main functions of the variable density plane cascade wind tunnel. The Reynolds number can be as low as 3.1×10⁵m^–1 so that the low Reynolds number experiments can be made easyly with the facility. The flow field debugging results satisfy the National military standard GJB 1179A—2012 of the specification for flow quality of high and low speed wind tunnels. It provides a key test platform for the study of the transonic, supersonic Mach number and low Reynolds number flow problems of the compressor and turbine cascades.
- plane cascade,
- wind tunnel,
- turbomachinery,
- Reynolds number,
- Mach number

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