CN109648288B

CN109648288B - Aeroengine low pressure turbine installation device

Info

Publication number: CN109648288B
Application number: CN201811550866.4A
Authority: CN
Inventors: 龙洋; 叶茂; 牛孝霞
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2018-12-18
Filing date: 2018-12-18
Publication date: 2021-03-12
Anticipated expiration: 2038-12-18
Also published as: CN109648288A

Abstract

The application discloses aeroengine low pressure turbine installation device, it includes: one end of the guide shaft is relatively fixed with the low-pressure turbine shaft; the switching section is arranged at the other end of the guide shaft and is fixed in an angular direction through a connecting piece; the centering device is fixed with the rotor, a centering sleeve is arranged between the centering device and the guide shaft and used for enabling the axis of the guide shaft to be coincident with the axis of the engine, and the centering sleeve and the guide shaft can move relatively on the axis of the engine; the top pulling device comprises a rotating section axially fixed with the guide shaft and a moving section in threaded fit with the centering device, and the rotating section and the moving section are axially fixed and can rotate relatively; the anti-twist device is provided with an anti-twist part, the anti-twist part is matched with the moving section to prevent the moving section from rotating, and the anti-twist device is relatively fixed on the stator casing of the engine. The device can improve the installation quality of the four-pivot bearing of the engine and improve the reliability of the engine; reduce bearing damage and prolong the service life of the bearing.

Description

Aeroengine low pressure turbine installation device

Technical Field

The application belongs to the technical field of aero-engine assembly, and particularly relates to an aero-engine low-pressure turbine installation device.

Background

As shown in fig. 1, an aircraft engine generally includes, in an airflow direction, a fan 100, an intermediate casing 200, a core 300, and a low pressure turbine 400, wherein the fan 100, the core 300, and the low pressure turbine 400 are all rotating components that need to be supported.

At present, the fulcrum layout of an aircraft engine is generally that a low-pressure rotor adopts a 0-2-1 supporting form, namely, a front end of the low-pressure rotor is provided with no fulcrum bearing, the middle of the low-pressure rotor is provided with 2 fulcrum bearings (fulcrums Z1 and Z2 are provided with bearings), a rear end of the low-pressure rotor is provided with 1 fulcrum (fulcrum Z5 is provided with a bearing), and a high-pressure rotor adopts a supporting form of 1 (fulcrum Z3 is provided with a bearing) -0-1 (fulcrum Z4 is provided with a bearing). The bearing of the fulcrum Z4 is an intermediate rolling rod bearing with a negative clearance (a roller is in interference fit with an outer ring) and is positioned between the high-pressure rotor and the low-pressure rotor, the inner ring and the outer ring of the bearing respectively belong to a low-pressure turbine unit body and a core machine, and the final assembly of the bearing is completed while the low-pressure turbine unit body is installed.

At present, the low-pressure turbine is assembled/disassembled by inserting the low-pressure turbine shaft 401 with the bearing inner ring and the rollers into the bearing outer ring or pulling the low-pressure turbine shaft out of the bearing outer ring. However, for the intermediary bearing with the negative play, in the whole process of single assembly, the specific angular positions of the roller and the outer ring inevitably generate linear sliding friction to cause the rubbing damage of the bearing, the friction coefficient is increased after the damage, the abrasion in the subsequent sliding process is accelerated, the diameter of the roller is reduced, the linear groove mark appears on the outer ring surface, the service life of the bearing is shortened, and meanwhile, the radial play of the bearing is changed to cause damage to the work of the rotor.

Disclosure of Invention

The application aims to provide a low-pressure turbine mounting device of an aircraft engine so as to solve any one of the problems.

The technical scheme of the application is as follows: an aircraft engine low pressure turbine mounting arrangement, comprising: one end of the guide shaft is relatively fixed with the low-pressure turbine shaft; the switching section is arranged at the other end of the guide shaft and is fixed in an angular direction through a connecting piece; the centering device is fixed with the rotor, a centering sleeve is arranged between the centering device and the guide shaft and used for enabling the axis of the guide shaft to be coincident with the axis of the engine, and the centering sleeve and the guide shaft can move relatively on the axis of the engine; the top pulling device comprises a rotating section axially fixed with the guide shaft and a moving section in threaded fit with the centering device, and the rotating section and the moving section are axially fixed and can rotate relatively; the anti-twist device is provided with an anti-twist part, the anti-twist part is matched with the moving section to prevent the moving section from rotating, and the anti-twist device is relatively fixed on the stator casing of the engine.

Further, the method also comprises the following steps: the rotor and stator fixing clamp is respectively and relatively fixed with the rotor and the stator of the low-pressure turbine, so that the axis of the rotor and the axis of the stator of the low-pressure turbine are overlapped and axially fixed; the rear casing lifting appliance is fixed on the low-pressure turbine stator casing; the gravity center adjustable lifting appliance is matched with the rear casing lifting appliance and used for adjusting the axial position of a lifting point to enable the lifting point to coincide with the projection of the gravity center of the low-pressure turbine on the horizontal plane.

The device can improve the installation quality of the four-pivot bearing of the engine and improve the reliability of the engine; reduce bearing damage and prolong the service life of the bearing.

Drawings

In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.

FIG. 1 is a schematic illustration of an aircraft engine configuration.

FIG. 2 is a schematic view of the mounting apparatus of the present application mounting a low pressure turbine.

Fig. 3 is a schematic structural diagram of the mounting device of the present application.

Fig. 4 is a side view of the mounting device of the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.

In order to solve the problems that the current aeroengine low-pressure turbine installation method damages a four-pivot bearing and reduces the service life of the bearing, the application provides the aeroengine low-pressure turbine installation device which can effectively reduce the damage to the bearing in the installation process.

2-4, the installation and rotation of the low-pressure turbine are realized by the low-pressure turbine installation device of the aeroengine, and are realized by matching with a crane and a torque wrench.

The aeroengine low pressure turbine installation device of this application guide shaft 5, changeover portion 2, centring means 4, draw top mounted putting 3 and anti-device of turning round 1. The guide shaft 5 is fixed to the low-pressure turbine shaft 401 with its axis coinciding with the low-pressure turbine axis to transmit the motion of the low-pressure turbine shaft to the outside of the engine. The centering device 4 is fixed with the fan disc 101 and is connected with the fan shaft 102 through sleeve teeth, and the inner diameter of the centering device is provided with an internal thread; the external thread arranged on the outer diameter of the rear part of the top pulling device 3 is matched with the centering device 4 to form thread transmission, the top pulling device and the front part of the centering device 4 can rotate relatively and simultaneously ensure the consistency of axial movement, and the front part of the top pulling device 3 is connected with the guide shaft 5 through a quick release pin; the anti-twisting device 1 is fixed on the stator casing 6 and limits the rotation of the rear part of the top pulling device 3; the switching section 2 is fixed with a guide shaft 5 through a quick-release pin to provide an interface for a wrench or a torque amplifier.

In addition, the lifting device also comprises a rotor and stator fixing clamp 8, a rear casing lifting appliance 9 and an adjustable gravity center lifting appliance 7. The rotor and stator fixing tool 8 is used for realizing axial fixing and radial fixing of the rotor and stator and allowing the rotor and stator to rotate around an axis; the rear casing hanger 9 fixes the rear mounting edge of the low-pressure turbine casing and is connected with the adjustable gravity center hanger 7, and the low-vortex axis is adjusted to be coincident with the axis of the core machine 300 by adjusting the lifting point position of the hanger and matching with an upward force F provided by a crane.

The installation device of this application motion process as follows: the spanner is rotated to drive the spanner switching section, and the guide shaft is driven by the quick release pin; the guide shaft drives the front part of the push-pull device to rotate through the quick release pin and simultaneously drives the low-vortex rotor to rotate; the low-vortex shaft drives the fan shaft to synchronously rotate through the spline; the fan shaft drives the fan disc through the bolt; the centering device synchronously rotates through the connection of the fan shaft sleeve teeth and the fan disc; because the thread pair is arranged between the pulling and jacking device and the centering device, and the rear angular position of the pulling and jacking device is fixed by the antitorque arm, the pulling and jacking device horizontally moves under the combined action of the antitorque arm and the threads of the centering device; because the top pulling device is fixed with the guide shaft through the quick-release pin, the guide shaft and the low-pressure turbine are driven to translate together, and rotary feeding is realized.

This application is at low pressure turbine installation, dismantlement in-process, when four fulcrum bearing rollers and outer loop contact, makes low pressure turbine take four fulcrum inner rings to feed while rotatory to with the whole even participation friction of whole cylinder of four fulcrum bearing rollers and outer loop, thereby shorten the friction sliding distance of former friction position by a wide margin, and then reduce the degree of wear of former friction position, improve the life of bearing. The mounting quality of the four-fulcrum bearing of the engine is improved, and the reliability of the engine is improved; reduce bearing damage and prolong the service life of the bearing.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. An aircraft engine low pressure turbine mounting arrangement, comprising:

one end of the guide shaft (5) is relatively fixed with the low-pressure turbine shaft (401);

the switching section (2) is arranged at the other end of the guide shaft (5) and fixed in an angular direction through a connecting piece;

the centering device (4) is fixed with the rotor, a centering sleeve is arranged between the centering device (4) and the guide shaft (5) and used for enabling the axis of the guide shaft to coincide with the axis of the engine, and the centering sleeve and the guide shaft can move relatively on the axis of the engine;

the device comprises a top pulling device (3), wherein the top pulling device (3) comprises a rotating section (31) axially fixed with a guide shaft (5) and a moving section (32) in threaded fit with a centering device (4), and the rotating section (31) and the moving section (32) are axially fixed and can relatively rotate;

the anti-twisting device (1), the anti-twisting device (1) is provided with an anti-twisting part (11), the anti-twisting part (11) is matched with the moving section (32) to prevent the moving section (32) from rotating, and the anti-twisting device (1) is relatively fixed on a stator casing; and

the rotor and stator fixing clamp (8) is respectively and relatively fixed with the rotor and the stator of the low-pressure turbine, so that the axis of the rotor and the axis of the stator of the low-pressure turbine are overlapped and axially fixed;

the rear casing lifting appliance (9), the rear casing lifting appliance (9) is fixed on the stator casing (6) at one end of the low-pressure turbine;

the gravity center adjustable lifting appliance (7) is matched with the rear casing lifting appliance (9) and used for adjusting the axial position of a lifting point so that the lifting point coincides with the projection of the gravity center of the low-pressure turbine on the horizontal plane.