CN212744737U

CN212744737U - Aeroengine bearing support

Info

Publication number: CN212744737U
Application number: CN202021559021.4U
Authority: CN
Inventors: 冯泽林; 钱原吉; 于大千; 张权; 罗京帅; 郁秋龙
Original assignee: Jiangsu Yuanqing Power Technology Co ltd
Current assignee: Jiangsu Yuanqing Power Technology Co ltd
Priority date: 2020-07-30
Filing date: 2020-07-30
Publication date: 2021-03-19
Anticipated expiration: 2030-07-30

Abstract

The utility model discloses an aeroengine bearing belongs to aeroengine accessory field, and its technical scheme main points are inside outer loop barrel and inner skleeve are located the outer loop barrel to both coaxial settings, be provided with a plurality of extension boards between inner skleeve and the outer loop barrel, the inner skleeve links to each other through a plurality of extension boards with the outer loop barrel, the utility model has the advantages of have splendid wholeness, better structural performance satisfies the requirement of long-time work in harsh environment.

Description

Aeroengine bearing support

Technical Field

The utility model relates to an aeroengine accessory field, in particular to aeroengine bearing.

Background

An aero-engine (aero-engine) is a highly complex and precise thermal machine, is used as the heart of an airplane, is not only the power for flying the airplane, but also an important driving force for promoting the development of aviation industry, and each important change in human aviation history is inseparable from the technical progress of the aero-engine. In the 21 st century, the development of aero-engines is further accelerated, and a new significant revolution is brought to the field of human aviation. Conventional aircraft engines are moving toward geared engines, variable cycle engines, multi-electric engines, and intercooled regenerative engines, and the development of these engines will make future aircraft faster, taller, farther, more economical, and more reliable.

The bearing support is a commonly used matching part in an aircraft engine, and mainly plays a role in fixing a bearing. Because the operating environment of the aircraft engine is severe, the used bearing support has higher performance requirements, the large-scale parts in the traditional bearing support are generally formed by split casting, the integrity is poor, and cracks are easy to occur at split joints, so that the structural performance of the bearing support cannot meet the requirement of long-time operation in the severe environment, and the bearing support with better structural performance is required.

SUMMERY OF THE UTILITY MODEL

The utility model aims at providing an aeroengine bearing, its advantage lies in having splendid wholeness, and better structural performance satisfies the requirement of working for a long time in harsh environment.

The above technical purpose of the present invention can be achieved by the following technical solutions:

the utility model provides an aeroengine bearing support, includes outer loop barrel and inner skleeve, and the inner skleeve is located the outer loop barrel inside to both coaxial settings, be provided with a plurality of extension boards between inner skleeve and the outer loop barrel, inner skleeve and outer loop barrel pass through a plurality of extension boards and link to each other.

Furthermore, the outer ring barrel comprises an outer ring upper section barrel and an outer ring base, the outer ring upper section barrel is connected with the outer ring base in a welding mode, the outer ring upper section barrel and the outer ring base are integrally cast, one end of the supporting plate is connected with the inner wall of the outer ring base, and the outer wall of the inner sleeve at the other end of the supporting plate is connected with the outer wall of the inner sleeve.

Furthermore, a lantern ring is welded on the outer side of the outer ring upper section cylinder.

Furthermore, the support plate is arranged in a uniform circumference mode through the central shaft of the inner sleeve, and the support plate is arranged in an inclined mode.

Furthermore, an upper cover plate and a lower cover plate are respectively arranged at two ends of the inner sleeve, the upper cover plate and the lower cover plate are annular, and the area of the lower cover plate is larger than that of the upper cover plate.

To sum up, the utility model discloses following beneficial effect has:

1. the inner sleeve, the outer ring upper section cylinder and the outer ring base are integrally cast and formed, so that the integrity is excellent, the condition that the split connection part is broken is avoided, and the structural performance of the bearing support is further improved;

2. the inner sleeve and the outer ring barrel are connected through the support plate, integrity is further improved, when the bearing rotates, the whole stress of the support is uniform, and fracture caused by local stress concentration is reduced.

Drawings

FIG. 1 is a schematic view of an aircraft engine bearing mount.

In the figure, 1, an outer ring cylinder body; 11. an outer ring upper section cylinder; 12. an outer ring base; 2. an inner sleeve; 21. a support plate; 22. an upper cover plate; 23. a lower cover plate.

Detailed Description

The present invention will be described in further detail with reference to the accompanying drawings.

In which like parts are designated by like reference numerals. It should be noted that the terms "front," "back," "left," "right," "upper" and "lower" used in the following description refer to directions in the drawings, and the terms "bottom" and "top," "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component.

Example (b): an aircraft engine bearing support is shown in figure 1 and comprises an outer ring cylinder body 1 and an inner sleeve 2, wherein the inner sleeve 2 is positioned inside the outer ring cylinder body 1 and is coaxially arranged with the outer ring cylinder body 1, a plurality of support plates 21 are arranged between the inner sleeve 2 and the outer ring cylinder body 1, and the support plates 21 connect the outer ring cylinder body 1 and the inner sleeve 2 into a whole.

The inner sleeve 2 is formed by integral casting. An upper cover plate 22 and a lower cover plate 23 are respectively arranged at two ends of the inner sleeve 2, and the upper cover plate 22 and the lower cover plate 23 are annular. The upper cover plate 22 extends outwards from the inner sleeve 2 and is provided with a circle of mounting holes in the extension part. The lower cover plate 23 has a larger area than the upper cover plate 22, and a portion of the lower cover plate 23 extends outward and another portion extends inward, and the extending portions are provided with mounting holes.

The outer ring barrel 1 comprises an outer ring upper section barrel 11 and an outer ring base 12, and the section barrel and the outer ring base 12 are connected in a welding mode. The outer wall of the outer ring upper section cylinder body 11 is welded with a lantern ring. The outer edge of the outer ring base 12 is provided with a group of positioning holes.

The support plates 21 are uniformly and circumferentially arranged on the central shaft of the inner sleeve 2, one ends of the support plates 21 are connected with the inner wall of the outer ring base 12, and the outer walls of the inner sleeve 2 are connected with the other ends of the support plates 21. The support plate 21 is obliquely arranged, and a triangle-like support structure is formed by the inner sleeve 2 and the outer ring base 12, so that the structural stability is better.

The manufacturing process of the bearing support comprises the following steps: 1: the outer ring base 12, the inner sleeve 2, the upper cover plate 22 and the lower cover plate 23 are investment cast in one piece.

2: and (4) forging the outer ring upper section cylinder body 11.

3: and brazing the outer ring upper section cylinder 11 and the outer ring base 12.

4: and (5) argon arc welding a lantern ring.

5: and processing corresponding positioning holes and mounting holes on the bearing support.

6: and coating a damping coating on the bearing support.

The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications to the present embodiment without inventive contribution as required after reading the present specification, but all of them are protected by patent laws within the scope of the claims of the present invention.

Claims

1. An aeroengine bearing support which characterized in that: the inner sleeve (2) is located inside the outer ring cylinder (1) and is coaxially arranged with the outer ring cylinder (1), a plurality of support plates (21) are arranged between the inner sleeve (2) and the outer ring cylinder (1), and the inner sleeve (2) is connected with the outer ring cylinder (1) through the support plates (21).

2. An aircraft engine bearing carrier according to claim 1, wherein: the outer ring barrel (1) comprises an outer ring upper section barrel (11) and an outer ring base (12), the outer ring upper section barrel (11) is connected with the outer ring base (12) in a welding mode, the outer ring upper section barrel (11) and the outer ring base (12) are integrally cast, one end of the support plate (21) is connected with the inner wall of the outer ring base (12), and the outer wall of the inner sleeve (2) at the other end of the support plate (21) is connected.

3. An aircraft engine bearing carrier according to claim 2, wherein: and a lantern ring is welded on the outer side of the outer ring upper section cylinder (11).

4. An aircraft engine bearing support according to claim 1, characterised in that the struts (21) are arranged in a uniform circumferential arrangement about the central axis of the inner sleeve (2), the struts (21) being arranged obliquely.

5. An aircraft engine bearing carrier according to claim 1, wherein: an upper cover plate (22) and a lower cover plate (23) are respectively arranged at two ends of the inner sleeve (2), the upper cover plate (22) and the lower cover plate (23) are annular, and the area of the lower cover plate (23) is larger than that of the upper cover plate (22).