Aviation engine low-pressure turbine installation device

Abstract

The invention discloses an aviation engine low-pressure turbine installation device. The aviation engine low-pressure turbine installation device comprises a guide shaft, a transfer segment, a centring device, a pulling jacking device and a reverse twist device, wherein one end of the guide shaft is relatively fixed with a low-pressure turbine shaft; the transfer segment is arranged at the other end of the guide shaft and is angularly fixed through a connection part; the centring device is fixed with a rotor, a centring sleeve is arranged between the centring device and the guide shaft to be used for making the axis of the guide shaft coincide with that of an engine, and the centring sleeve and the guide shaft can move relatively on the axis of the engine; the pulling jacking device comprises a rotating segment axially fixed with the guide shaft and a moving segment in screw-thread fit with the centring device, and the rotating segment and the moving segment are axially fixed and can rotate relatively; and the reverse twist device is provided with a reverse twist portion, the reverse twist portion is matched with the moving segment to be used for preventing rotating of the moving segment, and the reverse twist device is relatively fixed to an engine stator casing. By means of the aviation engine low-pressure turbine installation device, the installation quality of engine four fulcrum bearings can be improved, and the engine reliability is improved; and bearing damage is reduced, and the service lives of the bearings are prolonged.

Description

technical field [0001] The application belongs to the technical field of aero-engine assembly, and in particular relates to an aero-engine low-pressure turbine installation device. Background technique [0002] like figure 1 As shown, an aero engine generally includes a fan 100, an intermediate casing 200, a core engine 300 and a low-pressure turbine 400 along the airflow direction, wherein the fan 100, the core engine 300 and the low-pressure turbine 400 are all rotating parts and need to be supported. [0003] At present, for the fulcrum layout of aero-engines, the low-pressure rotor usually adopts a 0-2-1 support form, that is, there is no fulcrum bearing at the front end of the low-pressure rotor, two fulcrum bearings in the middle (the fulcrum Z1 and Z2 set the bearings), and one fulcrum at the rear end (fulcrum Z5 sets the bearing), and the high-pressure rotor adopts the support form of 1 (the fulcrum Z3 sets the bearing)-0-1 (the fulcrum Z4 sets the bearing). Among ...

AI Technical Summary

Problems solved by technology

However, for intermediate bearings with negative clearance, linear sliding friction will inevitably occur at a specific angular position between the roller and the outer ring during the entire process of single assembly, resulting in scratches and damage to the bearing, and the friction coefficient will increase after the damage , to accelerate the wear in the subsequent sliding process, resulting in a smaller diameter of the rollers, linear grooves appear on the outer ring surface, reducing the life of the bearing, and at the same time, due to the change of the radial clearance of the bearing, it will bring harm to the work of the rotor

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