CN112110328A

CN112110328A - Aircraft engine turbine disk hoist

Info

Publication number: CN112110328A
Application number: CN201910539954.2A
Authority: CN
Inventors: 陈寿宇; 涂卫强; 李明; 姚星; 胡一廷
Original assignee: AECC Commercial Aircraft Engine Co Ltd
Current assignee: AECC Commercial Aircraft Engine Co Ltd
Priority date: 2019-06-21
Filing date: 2019-06-21
Publication date: 2020-12-22

Abstract

The invention relates to an aircraft engine turbine disk lifting appliance, which comprises: a flexible member (1) which is wound around the turbine disk (3) and is detachably connected at a first end and a second end thereof; and a connecting member (2) connected to the flexible member (1) and used for connecting a hoisting device. By applying the technical scheme of the invention, the problem that the turbine disc of the aero-engine is inconvenient to move in the prior art is solved.

Description

Aircraft engine turbine disk hoist

Technical Field

The invention relates to the field of aircraft engine assembling tools, in particular to a lifting appliance for a turbine disc of an aircraft engine.

Background

The weight of the turbine disc of the aircraft engine is about 70Kg, and a hanger mounting structure is not arranged on the outer contour of the turbine disc. Because the weight of the disc is large, the disc is difficult to move manually in the assembling or maintaining process, and the lifting and moving of the turbine disc are usually realized by adopting a lifting appliance with an internal expansion structure. The internal expansion type lifting appliance comprises a base body, a moving component and a driving part, wherein the moving component can move relative to the base body in the radial direction of the turbine disc in the direction away from the base body, the driving part is used for driving the moving component to move relative to the base body, and the driving part can be a threaded driving mechanism. When the internal expansion type lifting appliance is used for lifting the turbine disc, the moving part is firstly adjusted to be close to the base body, then the lifting appliance is inserted into the central hole of the turbine disc, and finally the moving part is driven towards the direction far away from the base body so that the moving part abuts against the peripheral wall of the central hole, and therefore the lifting appliance and the turbine disc are connected together. The internal expansion type lifting appliance is complex, and the requirement in the operation process is high, so that the assembly or maintenance efficiency of the turbine is low.

Disclosure of Invention

The invention aims to provide a lifting appliance for an aero-engine turbine disc, which aims to solve the problem that the aero-engine turbine disc is inconvenient to move in the prior art.

According to an aspect of an embodiment of the present invention, there is provided an aircraft engine turbine disk hanger, comprising:

a flexible member for being wound around the turbine disk and detachably connected at first and second ends thereof; and

and the connecting part is connected with the flexible part and is used for connecting the hoisting equipment.

Alternatively, the flexible member is configured to be nestable in a catch groove extending circumferentially of the turbine disc.

Optionally, the connecting member is perpendicular to the plane of the loop defined by the flexible members connected end to end.

Optionally, the flexible member comprises a chain.

Alternatively, the chain comprises a plurality of links connected in series, adjacent two links being detachably connected.

Optionally, the flexible component further comprises an intermediate connector for connecting two adjacent links, the intermediate connector being detachably connected to the links.

Alternatively, the ends of the links are provided with recesses, into which one end of the intermediate connecting member is inserted and connected with the links by means of hinge shafts.

Alternatively, the links at the first end of the flexible member and the intermediate links at the second end of the flexible member are connected by a pluggable pin.

Optionally, the chain link is provided with a mounting structure for mounting the connecting member.

Optionally, the mounting structure comprises a threaded hole.

By applying the technical scheme of the invention, the problem that the turbine disc of the aero-engine is inconvenient to move in the prior art is solved.

Other features of the present invention and advantages thereof will become apparent from the following detailed description of exemplary embodiments thereof, which proceeds with reference to the accompanying drawings.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 shows a schematic structural view of a turbine disc and a spreader of an aircraft engine according to an embodiment of the invention;

FIG. 2 shows a schematic structural view of the cross section of FIG. 1;

FIG. 3 shows a schematic structural diagram of an aircraft engine turbine disk sling according to an embodiment of the invention;

FIG. 4 shows a schematic structural view of a flexible component of an aircraft engine turbine disk sling according to an embodiment of the invention; and

fig. 5 shows a schematic structural view of a flexible part of an aircraft engine turbine disk hanger according to an embodiment of the invention in a straightened state.

In the figure:

1. a flexible member; 11. a chain link; 12. an intermediate connecting member; 13. hinging a shaft; 14. a mounting structure; 2. a connecting member; 3. a turbine disk; 4. and (7) a pin shaft.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Fig. 1 shows a schematic structural view of a turbine disk and a spreader of an aircraft engine of the present embodiment, fig. 2 shows a schematic structural view of a cross section of fig. 1, and fig. 3 shows a schematic structural view of the spreader of the present embodiment.

As shown in fig. 1 to 3, the aircraft engine turbine disk hanger of the present embodiment includes a flexible member 1 that can be disposed around the circumference of a turbine disk 3, and a connecting member 2 that is connected to the flexible member 1 and is used to connect a hoisting device. The first and second ends of the flexible member 1 are detachably connected.

When the lifting appliance of the embodiment is used for moving the turbine disc 3 of the aircraft engine, the flexible part 1 in a free state is firstly wound on the turbine disc, then the first end and the second end of the flexible part 1 are connected, and finally the lifting device moves the turbine disc 3 of the aircraft engine through the connecting part 2.

In order to prevent the flexible member 1 from moving in the axial direction of the turbine disk 3, the flexible member 1 is configured to be fittable in a catch groove extending in the circumferential direction of the turbine disk 3, the catch groove being located on the circumferential surface of the turbine disk 3 and extending in the circumferential direction of the turbine disk 3.

In some embodiments, the flexible member 1 is located below a stopper member on the circumferential surface of the turbine disk 3, which can stop the movement of the flexible member 1, to prevent the flexible member 1 from moving in the axial direction of the turbine disk 3 when the turbine disk 3 is moved.

In some embodiments, the flexible member 1 surrounds the turbine disk 3 on a smooth circumferential surface, and the flexible member 1 is restricted from moving in the axial direction of the turbine disk 3 by a frictional force. Preferably, when the hoisting device moves the turbine disc 3, the plane of the ring surrounded by the flexible member 1 is arranged at an angle to the horizontal plane to increase the friction between the flexible member 1 and the turbine disc 3.

As shown in fig. 2 and 3, the connecting member 2 is perpendicular to the plane of the loop defined by the flexible members 1 connected end to end.

The connecting part 2 comprises a connecting rod connected to the flexible part 1 and a suspension ring connected to the end of the connecting rod remote from the flexible part 1. The lifting ring is used for connecting hoisting equipment.

Fig. 4 and 5 show a schematic structural view of the flexible member 1 of the present embodiment, and in conjunction with fig. 1 to 5, the flexible member 1 of the present embodiment includes a chain.

The chain comprises a plurality of chain links 11 connected in sequence, and two adjacent chain links 11 are detachably connected. Thus, the length of the flexible member 1 can be adjusted for different sizes of turbine discs 3, so that the spreader can be used to move turbine discs 3 of various sizes.

The flexible member 1 further includes an intermediate connecting member 12 for connecting adjacent two links 11, the intermediate connecting member 12 being detachably connected to the links 11.

The end of the chain link 1 is provided with a groove, and one end of the intermediate connecting member 12 is inserted into the groove and connected to the chain link 1 through a hinge shaft 13.

Both ends of the chain link 1 are provided with grooves, both ends of the chain link 1 are provided with first holes allowing the hinge shaft 13 to pass through, and both ends of the intermediate connecting member 12 are provided with second holes allowing the hinge shaft 13 to pass through.

The links 11 at the first end of the flexible member 1 and the intermediate connecting member 12 at the second end of the flexible member 1 are connected by a pluggable pin 4. Preferably, the pin 4 is a quick release pin.

The pin 4 may pass through a first hole in the link 1 and a second hole in the intermediate connector 12 to connect together the link 11 at the first end of the flexible member 1 and the intermediate connector 12 at the second end of the flexible member 1.

The chain link 1 is provided with a mounting structure 14 for mounting the connecting member 2. The mounting structure 14 includes a threaded hole. The connecting rod of the connecting part 2 is provided with a thread matched with the threaded hole.

The process of moving the turbine disc of the aircraft engine by adopting the lifting appliance of the embodiment comprises the following steps:

firstly, the pin shaft 4 is pulled out to enable the flexible part 1 of the hanger to be in a free state and form a linear or curved shape;

then, the flexible member 1 which becomes a straight line or a curve is enclosed in a groove of the turbine disc 3;

then, the intermediate connecting element 12 at the second end of the flexible element 1 is pushed into the recess of the link 11;

then, a pin shaft 4 is inserted into a first hole of a chain link 11 at a first end of the flexible component 1 and a second hole of an intermediate connecting piece 12 at a second end of the flexible component 1 to lock the annular groove of the turbine disc;

finally, a plurality of connecting members 2 are uniformly mounted on the flexible member 1 in the circumferential direction, and the turbine disk is mounted by a lifting rope.

By properly adding or reducing the chain links 11 and the middle connecting pieces 12, the circumference of the circle surrounded by the flexible parts 1 is changed, and the hoisting requirements of turbine disks of different models are met.

By loosening the pin shaft 4 on the chain, the flexible part 11 of the hanger is changed into a linear shape or a curved shape from an annular shape, and can be enclosed in a clamping groove in the turbine disc from the outer side, so that the turbine disc is lifted; the flexible component 1 comprises a plurality of connected chain links 11, and the circumference of a circle surrounded by a lifting appliance can be changed by properly increasing or reducing the number of the chain links 11, so that the lifting of different types of turbine disks (the diameters of grooves of the different types of turbine disks are different) can be met; the lifting appliance comprises a plurality of chain links 11 which are connected in sequence, the flexibility of the flexible component 1 is excellent, the flexible component can be abstracted to be a straight line or a curve, the requirement of the lifting appliance on the openness of an installation space is extremely low, and the lifting appliance can meet the lifting of a turbine disk in different occasions, for example, the turbine disk is positioned in an engine, the periphery of the turbine disk is limited by a stator casing, and the operation space is extremely narrow; the shape of the lifting appliance can be freely changed, the expansibility is extremely strong, and the lifting appliance can meet the requirement of lifting parts containing annular groove characteristics.

The lifting appliance of the aircraft engine has the following advantages:

1. the lifting appliance is simple in structure and can be operated by a single person in operation, and the clamping efficiency of the lifting appliance is improved;

2. the lifting appliance is locked into a ring shape through the quick release pin and clamped in the ring groove of the part, so that the structure is stable;

3. the assembly tool has simple structure and lower manufacturing and maintenance cost;

4. the application range of the lifting appliance is extremely wide, and the lifting appliance can meet the requirement of lifting parts containing annular groove characteristics.

The above description is only exemplary of the present invention and should not be taken as limiting the invention, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.

Claims

1. An aircraft engine turbine disc sling, comprising:

a flexible member (1) which is wound around the turbine disk (3) and is detachably connected at a first end and a second end thereof; and

and the connecting part (2) is connected with the flexible part (1) and is used for connecting hoisting equipment.

2. An aircraft engine turbine disc sling according to claim 1, wherein the flexible member (1) is configured to be nestable in a catch groove extending circumferentially along the turbine disc (3).

3. An aircraft engine turbine disc sling according to claim 1, characterised in that the connection member (2) is perpendicular to the plane of the loop enclosed by the flexible members (1) connected end to end.

4. An aircraft engine turbine disc sling according to claim 1, wherein said flexible member (1) comprises a chain.

5. An aircraft engine turbine disc sling according to claim 4, wherein the chain comprises a plurality of links (11) connected in series, two adjacent links (11) being detachably connected.

6. An aircraft engine turbine disc sling, according to claim 5, characterised in that the flexible member (1) further comprises an intermediate connection (12) for connecting two adjacent chain links (11), the intermediate connection (12) being detachably connected with the chain links (11).

7. Aeroengine turbine disk sling according to claim 6, wherein the end of the chain link (1) is provided with a groove, into which one end of the intermediate connection (12) is inserted and connected to the chain link (1) by means of an articulated shaft (13).

8. An aircraft engine turbine disc sling according to claim 6, characterised in that the chain links (11) at the first end of the flexible member (1) and the intermediate connection (12) at the second end of the flexible member (1) are connected by means of a pluggable pin (4).

9. Aeroengine turbine disk sling according to claim 5, wherein the chain link (11) is provided with a mounting structure (14) for mounting the connecting member (2).

10. The aircraft engine turbine disc sling according to claim 9, wherein the mounting structure (14) comprises a threaded hole.