A height-adjustable planar cascade test section

A technology of cascade test and test section, which is applied in engine test, machine/structural component test, jet engine test, etc. It can solve the problems of reduced test accuracy, high labor intensity, inconvenient operation, etc., and save test The effect of preparation time, high test accuracy and simple test preparation
CN113029575BActive Publication Date: 2022-04-26中国空气动力研究与发展中心空天技术研究所
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
中国空气动力研究与发展中心空天技术研究所
Publication Date
2022-04-26

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Abstract

The invention discloses a height-adjustable plane cascade test section. The plane cascade test section is a square body, including a shell, two test section disks installed side by side on the left and right in the shell, two wall plate assemblies installed up and down in the shell, and two sets of corresponding angle adjustments. The inner wall of the two test sections, the space between the two upper and lower wall plate assemblies and the two upper and lower length compensation plates is the test section; the space between the outer wall of the two test sections and the shell The space is the living room of the test section. The moving end of the angle adjuster drives the two upper and lower wall plate assemblies to rotate around the pin shaft to adjust the height and angle of the upper and lower wall plate assemblies of the test section. The planar cascade test section has comprehensive functions, convenient operation, simple positioning and high precision, which can save test preparation time and improve test efficiency.
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Description

technical field

[0001] The invention belongs to the field of aero-engine basic research test equipment, in particular to a height-adjustable plane cascade test section. Background technique

[0002] Aviation turbines (including fans / compressors and turbines) and gas turbines are key components for maintaining thermal cycles and generating thrust, and the aerodynamic shape of their rotor / stator blades determines the aerodynamic performance of aviation turbines and gas turbines. In order to design high-performance aerojet engines and gas turbines, it is necessary to study the design method and flow characteristics of the turbine at the cascade (two-dimensional airfoil) level. In order to conduct experimental research on cascade channel flow under real flight conditions on the ground, it is necessary to build ground equipment capable of simulating parameters such as the Mach number and Reynolds number of the cascade flow during actual flight, so as to ensure that it can be carr...

Claims

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