Supersonic speed test cabin for plane cascade high-altitude flow simulation

Abstract

The invention discloses a supersonic speed test cabin for plane cascade high-altitude flow simulation. The supersonic speed test cabin is a square body, two test section discs are parallel to the axis of the supersonic speed test cabin and are fixed on the lower surface in a shell in parallel, the front ends of the test section discs are connected with an airflow inlet flange of the shell, and the space among the inner walls of the two test section discs, an upper suction wall plate, a lower suction wall plate, an upper throttling wall plate and a lower throttling wall plate is a test section; the space between the outer walls of the two test section discs and the shell is a test section plenum chamber; the eight driving devices are vertically symmetrical, are respectively mounted on the upper and lower surfaces of the shell and the test disc, and are used for mounting and adjusting the upper and lower suction wallboards and the upper and lower throttling wallboards; Observation windows are installed in the center of left and right side walls of the shell. The supersonic speed test cabin is comprehensive in function, convenient to operate, simple in test preparation and high in test precision, the test preparation time can be saved, the flow field quality can be improved, the test efficiency can be improved, and plane cascade supersonic velocity flow simulation can be conveniently and quickly realized.

Description

technical field [0001] The invention belongs to the field of aero-engine basic research test equipment, and in particular relates to a supersonic speed test chamber used for high-altitude flow simulation of plane cascades. 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 the aerodynamic characteristics of cascade passage flow under real flight conditions on the ground, it is necessary to build ground equipment that can simulate parameters such as the Mach number and Reynolds...

AI Technical Summary

Problems solved by technology

At present, the test section of the flow simulation device used in supersonic cascade tests at home and abroad usually has the following shortcomings: First, the upper and lower suction plates do not have angle adjustment and control functions, and the flow direction angle of the test section cannot be automatically adjusted and corrected according to the actual measurement results. Lack of means to improve field quality

The second is the manual adjustment method commonly used in the tail plate, it is difficult to adjust the angle of the upper and lower tail plates in real time according to the static pressure distribution in front of the cascade during the test, so as to achieve the purpose of improving the flow field quality of the test; the manual operation of the tail plate needs to be paused Experiment, not only waste of gas source, but also low efficiency

The third is that the upper and lower baffles and the upper and lower restrictors do not have automatic angle adjustment and control functions. The commonly used manual adjustment method makes it difficult to adjust the upper and lower baffles and the upper and lower baffles in real time during the test process according to the static pressure ratio before and after the grid. The angle of the upper and lower restrictors realizes the change of the cascade from the clogged condition to the stalled condition, and quickly obtains the characteristic curve of the cascade; when the upper and lower baffles and the upper and lower restrictors are manually operated, the test needs to be suspended, which not only wastes air resources, but also reduces efficiency. The continuous static pressure ratio cascade characteristic curve cannot be obtained; Fourth, the test section has no resident structure, and most of them adopt the opening exhaust method, and the adjustment of the test back pressure cannot be realized through the injection method, and the simulation method for the test Reynolds number is single and the scope is limited , insufficient high-altitude simulation capabilities

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