Aero-engine nozzle adjusting mechanism

Abstract

The invention belongs to the technical field of aero-engine nozzle adjusting mechanism design, and particularly relates to an aero-engine nozzle adjusting mechanism. The aero-engine nozzle adjusting mechanism comprises multiple rocker arms, pull rods, multiple actuating cylinders, a supporting ring and multiple connecting rod structures; the rocker arms are hinged to the outer wall of a nozzle connecting cylinder and distributed in the circumferential direction; one end of each pull rod is correspondingly hinged to one rocker arm, and the other end is correspondingly hinged to the outer wall of one convergence piece; a cylinder body of each actuating cylinder is hinged to the outer wall of the nozzle connecting cylinder; each piston rod is correspondingly hinged to one rocker arm to drive the corresponding rocker arm to rotate around the hinged part of the corresponding rocker arm and the nozzle connecting cylinder, so that the corresponding convergence piece is driven to move through the corresponding pull rod; the periphery of the nozzle connecting cylinder is sleeved with the supporting ring; one end of each connecting rod structure is hinged to the supporting ring, the other end is correspondingly hinged to the outer wall of one expansion piece, and the axial effective length can be adaptively adjusted in the process that the corresponding expansion piece moves along with the corresponding convergence piece.

Description

technical field [0001] The application belongs to the technical field of design of an aero-engine nozzle adjustment mechanism, and in particular relates to an aero-engine nozzle adjustment mechanism. Background technique [0002] The nozzle is an important part of the aero-engine, which is used to expel the high-temperature and high-pressure gas after the turbine to expand and accelerate, thereby generating engine thrust. , one end of each converging piece is hinged at the outlet end of the nozzle connecting cylinder, distributed along the circumferential direction, and the adjacent converging pieces are in sealing contact to form the nozzle converging section, and the radial dimension of the nozzle converging section is away from the nozzle The direction of the connecting cylinder shrinks gradually to form the throat of the nozzle; one end of each expansion piece is correspondingly hinged on the other end of a convergent piece, and the adjacent expansion pieces are in seali...

AI Technical Summary

Problems solved by technology

[0003] During the working process of the aero-engine, in order to obtain better thrust performance, it is necessary to adjust the nozzle throat area and nozzle outlet area according to the actual working conditions. Currently, a convergent plate adjustment mechanism is designed to drive each convergent plate to wind and connect with the nozzle. The connecting part at the outlet end of the barrel rotates to realize the adjustment of the throat area of ​​the nozzle, and a plurality of connecting rods are designed to connect each expansion piece and the fixed end, and each expansion piece rotates under the drive of the corresponding convergent piece, thereby changing the nozzle outlet area , because the length of each connecting rod is fixed, when the nozzle throat area is constant, the nozzle outlet area is also determined, that is, there is a one-to-one correspondence between the nozzle outlet area and the nozzle throat area. To obtain the optimal thrust performance, in addition, the existing convergent plate adjustment mechanism is complex in structure, heavy in weight, poor in rigidity, and needs to occupy a large space. In order to synchronize the adjustment of each convergent plate, a complex synchronization mechanism is designed, and the load Larger, lower adjustment efficiency, hysteresis to the adjustment of the convergent plate, so that the change of the throat area of ​​the nozzle lags behind, limiting the improvement of engine performance

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