Variable attack angel apparatus for wind tunnel test of aircraft engine model

Abstract

Disclosed is a variable attack angel apparatus for a wind tunnel test of an aircraft engine model. A hydraulic motor is fixed to the right side of a frame, the rotation shaft of the hydraulic motor is connected with a first gear, the first gear is engaged with a second gear, the second gear and a third gear are fixed on a transmission shaft, the transmission shaft is fixed on the frame through a first bearing and a second bearing, the front side and the back side of the frame are connected with a mobile side plate respectively through a left arc guide pair and a right arc guide pair, the mobile side plate is fixedly connected with a workbench, a sector gear is fixed on the upper end surface of the right end of the mobile side plate, the third gear is engaged with the sector gear, the frame is provided with a self-lock mechanism, running mechanisms are installed at four corners of the frame, and the circle center of the left arc guide pair, the circle center of the right arc guide pair and the circle center of the sector gear are concentric and are disposed on a middle transverse line at the port surface of an inlet channel of the engine model. The variable attach angle apparatus can enable the attack angel of the engine model to be dynamically changed, and enables the result of the wind tunnel test of the aircraft engine model to be more accurate and reliable.

Description

technical field [0001] The invention relates to an aircraft engine model wind tunnel test variable attack angle device. Background technique [0002] Aerojet engines, no matter turbojet, turbofan or ramjet, are equipped with air inlets at the front and exhaust nozzles at the rear. The intake port is an important part of the engine. Its function is to convert the kinetic energy of the oncoming airflow into potential energy, reduce the incoming flow velocity to a speed suitable for the flame propagation speed in the combustion chamber, increase the airflow pressure and temperature, and provide the engine Provide the required air flow. Carry out a wind tunnel test on the engine model, that is, place the engine model on the angle of attack mechanism of the wind tunnel, and change the angle of the engine model (intake port) through the angle change of the angle of attack mechanism to study the impact of different airflow angles of attack on the intake air. The influence of the ...

AI Technical Summary

Problems solved by technology

Because it rotates around the platform, that is, the hinge axis in the middle of the engine model, the angle of attack changes, which will make the center of the air intake port surface at the front end of the engine far away from the center of the wind tunnel nozzle, and the air far away from the center of the wind tunnel nozzle. The uniformity of the flow field is poor, which is inconsistent with the uniform air flow field of the engine inlet port surface during the actual flight of the aircraft, which seriously affects the reliability and accuracy of the test

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