Shutter type special equipment for wake flow protection of aircraft engine

Abstract

The invention provides shutter type special equipment for wake flow protection of an aircraft engine, which comprises a barrier assembly, wherein the barrier assembly comprises more than two flow guide pieces; the flow guide piece comprises a flow guide structure I; the flow guide structure I is arranged upwards in an arc shape in the direction perpendicular to the flow direction of wake flow sprayed out of an aircraft from the wake flow sprayed out of the aircraft; the first flow guide piece extends upwards to form a second flow guide piece; the adjacent second flow guide pieces are arranged in parallel; an included angle of 80-90 degrees is formed between the second flow guide piece and the wake flow ejection direction of the aircraft; wake flow ejected by the aircraft enters an arc-shaped narrow strip slit through a flow guide inlet and then is discharged through a flow guide outlet; an included angle of 80-90 degrees is formed between the part, which is close to the second flow guide piece, of the arc-shaped narrow strip slit and the direction of the wake flow ejected by the aircraft; and the wake flow entering the arc-shaped narrow strip slit is discharged out of the flow guide outlet along an approximately vertical angle, so that wake flow with high-temperature heat is guided; and meanwhile, the discharged wake flow does not influence residents or workers behind the aircraft.

Description

technical field [0001] The invention relates to the field of aviation equipment, in particular to a louver-type aircraft engine wake protection special equipment. Background technique [0002] During the ground test of civil aircraft, a large amount of high-temperature and high-speed airflow will be generated at the tail of the aircraft. If the test cannot be carried out in an extremely open place, it will impact nearby workers or buildings, which has great potential safety hazards, and the noise generated during the test flight of the aircraft is also very high. It is not a nuisance, but a kind of sound pollution. [0003] In China, the patent number is 201720258330.X; the patent document with an announcement date of 2018.1.9 discloses a louver-type wind-acoustic barrier; There are at least two noise-absorbing blades that are rotatably connected to the supporting columns and used for sound absorption, sound insulation, flow diversion and flow disturbance by rotation betwee...

AI Technical Summary

Problems solved by technology

[0004] When the barrier is used in the ground test of the aircraft, the aircraft will be set in front of the barrier; the adjacent noise-absorbing blades will interact with the wake of the aircraft; that is, the adjacent noise-absorbing blades will interact with the wind flow in the same direction; The rotation directions of the adjacent muffling blades are consistent and rotate synchronously; when the adjacent muffling blades rotate at the same time, the narrow slit between adjacent muffling blades does not change. ; The adjacent noise-absorbing blades are arranged in parallel; that is, the narrow slits are in a straight line structure, which causes uneven air pressure when passing through the narrow slits, making the local pressure of the air too large; thereby shortening the service life of the barrier; at the same time This structure cannot play the role of accelerating the airflow leaving the narrow slit;

[0005] At the same time, the upper or lower parts of the noise-absorbing blades are inclined toward the leeward wind direction, that is, the noise-absorbing blades are inclined, and the noise-absorbing blades guide the airflow obliquely. Compared with the absence of barriers, this structure only improves the height of the wake; The wake flow will still affect the residents or staff behind the aircraft; the diversion effect is poor;

[0006] At the same time, the barrier is overlapped with the adjacent fixed windshield through the free edge of the noise-absorbing blade, so as to limit the rotation angle of the noise-absorbing blade; Next, the adjacent adjacent noise reduction blades appear parallel; at this time, the barrier cannot play a role in guiding the wake jet from the aircraft

Images