A puller for removing a fixed nozzle of a small aero-engine and its application method

Abstract

The invention discloses a puller for removing a fixed nozzle of a small aero-engine and a method for using the same. The puller supports a spherical base of a screw assembly and fixes it to the end of the tail cone of the inner nozzle of the engine, and adjusts the screw thread of the lower slider assembly. The sleeve moves downwards, so that the rubber part of the main bracket of the telescopic bracket assembly extends into the area between the internal nozzle and the fixed nozzle, and then adjusts the sliding cylinder of the upper slider assembly to move downwards, so that the rubber part of the front end of the main bracket is in contact with the fixed nozzle. The inner wall of the fixed nozzle is in contact with each other, so that the threaded sleeve moves upward, thereby driving the circumferential telescopic bracket assembly to move upward at the same time, and the fixed nozzle is pulled out from the outer culvert shell along the reverse course. The dismantling puller provided in this embodiment and its use method provide an adjustable dismantling puller by adopting a telescopic mechanism and a locking mechanism, etc., to ensure the smooth removal of the fixed nozzle, and to avoid impact and fatigue fracture of components, etc. damage.

Description

technical field [0001] The invention belongs to the field of aviation manufacturing engineering, and relates to a puller for removing a fixed nozzle of a small aeroengine and a use method thereof. Background technique [0002] At present, the tail nozzle of small aero-engines generally adopts a thin-walled fixed nozzle structure. Therefore, during the operation of the engine, the high-temperature and high-pressure gas in the flow channel can easily cause various deformations of the fixed nozzle and the outer shell that it contacts. The stagnation and adhesion caused the tightness of the fit to increase significantly, but at the same time, because the fixed nozzle is a tapered sleeve structure, there is no axial bearing surface required to meet the disassembly requirements. Therefore, when decomposing the fixed nozzle, it mainly relies on the rubber first. The hammer repeatedly strikes the outer wall of the nozzle outward along the circumferential direction, and then relies o...

AI Technical Summary

Problems solved by technology

[0002] At present, the tail nozzle of small aero-engines generally adopts a thin-walled fixed nozzle structure. Therefore, during the operation of the engine, the high-temperature and high-pressure gas in the flow channel can easily cause various deformations of the fixed nozzle and the outer shell that it contacts. The stagnation and adhesion caused the tightness of the fit to increase significantly, but at the same time, because the fixed nozzle is a tapered sleeve structure, there is no axial bearing surface required to meet the disassembly requirements. Therefore, when decomposing the fixed nozzle, it mainly relies on the rubber first. The hammer repeatedly strikes the outer wall of the nozzle outward along the circumferential direction, and then relies on the operator to clamp the walls on both sides of the nozzle to pull it out forcefully. risk

Secondly, once the thrust of a small aero-engine cannot meet the design requirements, it can only be adjusted by replacing the nozzle. Therefore, compared with other types of aero-engines, the frequency of disassembly and assembly of the fixed nozzle of the small aero-engine is extremely high, so the disassembly of the original fixed nozzle This method is difficult to meet the development needs of small aero-engines, which seriously affects the quality and efficiency of engine disassembly and its restoration assembly

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