Reverse thrust cascade test system and test reverse thrust cascade thereof

Abstract

One purpose of the invention is to provide a test reverse thrust cascade, which provides a basis for rapid test of different cascade exhaust areas. Another purpose of the invention is to provide a reverse thrust cascade test system which comprises the test reverse thrust cascade. In order to achieve the purpose, the test reverse thrust cascade comprises an outer frame, a plurality of blades and a linkage assembly. The outer frame is provided with a first matching part, the plurality of blades are respectively provided with a second matching part, the second matching part is detachably connected with the first matching part, the first matching part allows each blade to move along the first direction of the outer frame, the linkage assembly is respectively connected with each blade, and the linkage assembly is operated to simultaneously adjust the distance between the plurality of blades in the first direction.

Description

technical field [0001] The invention relates to a test system of reverse thrust cascade and the test system of reverse thrust cascade. Background technique [0002] The thrust reverser device is used to shorten the landing stroke distance of the aircraft, and it can also be used for the interrupted takeoff of the aircraft. The thrust reverser cascade is a key component for the thrust reverser device to change the direction of the exhaust flow of the engine to obtain reverse thrust. Therefore, the reverse thrust vane The design of the grid is very important for the high bypass ratio turbofan engine. like figure 1 Shows a partial schematic diagram of a turbofan engine with a large bypass ratio. When the aircraft lands, the thrust reverser works, and the airflow passes through the bypass flow channel 91, then through the reverse propulsion inlet 92, the reverse thrust cascade flow channel 93, and the reverse thrust outlet 94. Drain the engine. The front end of the thrust rev...

AI Technical Summary

Problems solved by technology

The existing test reverse thrust cascade has an integrated fixed structure and does not have adjustable characteristics. Therefore, one cascade aerodynamic test can only verify the axial arrangement of a single cascade. If it is necessary to verify the axial arrangement of multiple cascades, That is, the aerodynamic performance of reversed cascades with different cascade exhaust areas needs to be redesigned, manufactured and tested after the reversed cascades are retested, resulting in increased test costs and longer test periods, which in turn lengthen the entire cascade design cycle , not conducive to project development

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