CN115163206A

CN115163206A - Wheel disc with error proofing function

Info

Publication number: CN115163206A
Application number: CN202210902981.3A
Authority: CN
Inventors: 沈锡钢; 于连超; 李晓冲; 王�华; 高兴; 印雪梅
Original assignee: AECC Shenyang Engine Research Institute
Current assignee: AECC Shenyang Engine Research Institute
Priority date: 2022-07-29
Filing date: 2022-07-29
Publication date: 2022-10-11

Abstract

The application belongs to aeroengine manufacturing and designing field, in particular to rim plate with error proofing function includes: the outer wall surface of the wheel disc (1) is provided with a circumferential groove, the groove comprises a front wall and a rear wall, and the front wall and the rear wall are protruded inwards at the groove opening to narrow the groove opening; wherein the air flow of the aircraft engine flows from the front wall to the rear wall; the blade root of the rotor blade (2) is provided with a blade flange plate, the end surface of the blade flange plate is provided with a mounting boss, and the mounting boss is sunk into the open slot; wherein, the antetheca with the back wall is asymmetric structure, this application through with fluting designs into asymmetric structure, avoids rotor blade installation mistake's the condition.

Description

Wheel disc with error proofing function

Technical Field

The application belongs to the field of aero-engine design and manufacturing, and particularly relates to a wheel disc with a mistake proofing function.

Background

When the flow path of the engine is relatively flat, the outer edge of the wheel disc is usually designed to be equal in height, the rotor blade with the structure has the defect that the front part and the rear part are easy to reverse in the assembling process, the inspection and re-assembly cost and period are increased, and the working efficiency is reduced; if not detected, blade reversal during operation can have a severe impact on performance.

Disclosure of Invention

In order to solve the above problem, the present application provides a wheel disc with an error-proofing function for connecting rotor blades of an aircraft engine, comprising:

the outer wall surface of the wheel disc is provided with a circumferential groove, the groove comprises a front wall and a rear wall, the front wall and the rear wall are protruded inwards at the groove, and the protrusion forms a narrow opening of the groove; wherein the air flow of the aircraft engine flows from the front wall to the rear wall;

the blade root of the rotor blade is provided with a blade flange plate, the end surface of the blade flange plate is provided with a mounting boss, and the mounting boss is sunk into the open slot;

wherein the front wall and the rear wall are of asymmetric structure.

Preferably, the asymmetric structure is specifically: the front wall has a height H1 less than the rear wall height H2, and the vane platform has a ledge at the location of the front wall.

Preferably, the height H3 of the boss satisfies: h1+ H3= H2.

Preferably, the mounting boss and the front wall have a first overlapping surface, the mounting boss and the rear wall have a second overlapping surface, and the first overlapping surface and the second overlapping surface have different heights.

Preferably, the height of the gap between the blade edge plate and the front wall is equal to the height of the gap between the blade edge plate and the rear wall.

Preferably, the difference in height between the first overlapping surface and the second overlapping surface is greater than the clearance distance between the vane platform and the front wall.

Preferably, the slot has an installation notch for installing the installation boss into the slot.

Preferably, the clearance between the boss and the front wall is equal to the clearance between the vane edge plate and the rear wall.

Preferably, the height difference between the front wall and the rear wall is greater than the gap

The advantages of the present application include: this application is through will fluting designs into asymmetric structure, avoids rotor blade installation mistake's the condition.

Drawings

Fig. 1 is a schematic view of a wheel disc having an error proofing function according to embodiment 1 of the present application;

fig. 2 is a schematic view of a wheel disc having an error proofing function according to embodiment 2 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 the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the accompanying drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.

Example 1:

in order to solve the above-mentioned problems, as shown in fig. 1, the present application provides a wheel disc having an error-proofing function for connecting rotor blades of an aircraft engine, comprising:

the aircraft engine comprises a wheel disc 1, wherein a circumferential groove is formed in the outer wall surface of the wheel disc 1, the groove comprises a front wall and a rear wall, the front wall and the rear wall are protruded inwards at the groove position to narrow the groove, the protrusion forms a narrow opening of the groove, and the airflow of the aircraft engine flows from the front wall to the rear wall;

the blade root of the rotor blade 2 is provided with a blade flange plate, the end surface of the blade flange plate is provided with a mounting boss, and the mounting boss is sunk into the open slot; when the mounting boss is connected with the open slot of the wheel disc 1; when the wheel disc 1 rotates, the bulge at the notch is lapped with the mounting boss under the action of centrifugal force;

wherein the front wall and the rear wall are of asymmetric structure.

In some alternative embodiments, the mounting boss and the front wall have a first overlapping surface, the mounting boss and the rear wall have a second overlapping surface, and the first and second overlapping surfaces have different heights.

In some alternative embodiments, the height of the gap between the vane platform and the front wall is equal to the height of the gap between the vane platform and the rear wall.

In some alternative embodiments, the difference in height between the first and second overlapping surfaces is greater than the clearance distance between the vane platform and the front wall.

In some alternative embodiments, the slot has a mounting notch for mounting the mounting boss into the slot.

Example 2

the wheel disc comprises a wheel disc 1, wherein a circumferential groove is formed in the outer wall surface of the wheel disc 1, the groove comprises a front wall and a rear wall, and the front wall and the rear wall are protruded inwards at a groove opening to narrow the groove opening; wherein an air flow of the aircraft engine flows from the front wall to the rear wall;

the blade root of the rotor blade 2 is provided with a blade flange plate, the end surface of the blade flange plate is provided with a mounting boss, and the mounting boss is sunk into the open slot;

wherein the front wall and the rear wall are in an asymmetric structure.

In some alternative embodiments, the asymmetric structure is in particular: the front wall has a height H1 less than the rear wall height H2, and the vane platform has a ledge at the location of the front wall.

In some alternative embodiments, the height H3 of the boss satisfies: h1+ H3= H2;

in some alternative embodiments, the clearance between the boss and the front wall is equal to the clearance between the vane platform and the rear wall.

In some alternative embodiments, the difference in height between the front wall and the rear wall is greater than the gap.

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. A wheel disc with error protection for connecting rotor blades of an aircraft engine, comprising:

the outer wall surface of the wheel disc (1) is provided with a circumferential groove, the groove comprises a front wall and a rear wall, the front wall and the rear wall are protruded inwards at the groove, and the protrusion forms a narrow groove opening; wherein the air flow of the aircraft engine flows from the front wall to the rear wall;

the blade root of the rotor blade (2) is provided with a blade flange plate, the end surface of the blade flange plate is provided with a mounting boss, and the mounting boss is sunk into the open slot;

wherein the front wall and the rear wall are of asymmetric structure.

2. The wheel disc with error proofing function according to claim 1, characterized in that said asymmetrical structure is in particular: the front wall has a height H1 less than the rear wall height H2, and the vane platform has a ledge at the location of the front wall.

3. The wheel disc with error proofing function according to claim 2, wherein the height H3 of the boss satisfies: h1+ H3= H2.

4. The error-proof roulette wheel disc as set forth in claim 1, wherein said mounting boss and said front wall have a first overlapping surface, said mounting boss and said rear wall have a second overlapping surface, and the first and second overlapping surfaces have different heights.

5. The mistake proofing wheel disc of claim 4 wherein the height of the gap between the vane platform and the front wall is equal to the height of the gap between the vane platform and the back wall.

6. The mistake resistant wheel disc of claim 5 wherein the difference in height between the first and second overlapping surfaces is greater than the clearance distance between the platform and the front wall.

7. The error-proofing wheel disc of claim 2, wherein said slot has a mounting notch for mounting said mounting boss into said slot.

8. The error proofing wheel disc of claim 3 wherein the clearance between said boss and said front wall is equal to the clearance between said platform and said back wall.

9. The error-proofing wheel disc according to claim 8, wherein the difference between the height of said front wall and the height of said rear wall is greater than said gap.