CN-116877213-B - A dish edge cone shell clamping stagnation structure for preventing aeroengine turbine is changeed

CN116877213BCN 116877213 BCN116877213 BCN 116877213BCN-116877213-B

Abstract

The invention provides a disc edge cone shell clamping structure for preventing an aeroengine turbine from over-rotating, which comprises a disc edge baffle and a cone shell baffle, wherein the disc edge baffle is arranged at the rear side of a turbine disc, the head of the disc edge baffle is provided with a petal-shaped outer ring surface, the cone shell baffle is arranged on an oil cavity bushing, and the shoulder of the cone shell baffle is provided with a petal-shaped inner ring surface. In the mounting state and the normal left-side state of the engine, the outer annular surface of the head part of the disc edge baffle plate is opposite to the front and back of the inner annular surface of the shoulder part of the cone shell baffle plate, and a certain distance is formed between the outer annular surface of the head part of the disc edge baffle plate and the inner annular surface of the shoulder part of the cone shell baffle plate in the axial direction.

Inventors

HONG JIE
LI CHAO
ZHANG JIAN
CHEN XUEQI
WANG YONGFENG
MA YANHONG

Assignees

北京航空航天大学

Dates

Publication Date: 20260505
Application Date: 20230824

Claims (4)

1. The disc edge cone shell clamping structure for preventing the turbine of the aeroengine from overturning is characterized by comprising a disc edge baffle and a cone shell baffle, wherein the disc edge cone shell clamping structure is arranged at a low-pressure turbine part and limits the rotating speed of the low-pressure turbine rotor part after a low-pressure rotating shaft breaks so as to prevent the low-pressure turbine rotor part from overturning and a low-pressure turbine disc from overturning; The disc edge baffle is provided with a bottom mounting edge, a head axial end surface and a top outer annular surface, wherein the top outer annular surface is provided with a certain taper and is wavy, and first pits and first bosses are uniformly distributed on the top outer annular surface at intervals in the circumferential direction; the cone shell baffle is provided with a bottom mounting edge, a head joint edge and a shoulder inner annular surface, wherein the shoulder inner annular surface is provided with taper, but smaller than the taper of the top outer annular surface, the shoulder inner annular surface is wavy, and second pits and second bosses are uniformly distributed on the shoulder inner annular surface at intervals in the circumferential direction; The disc edge baffle is connected with the turbine disc mounting edge through a second bolt at the position of the bottom mounting edge, so that self fixed mounting is realized; The head joint edge of the cone shell baffle is in lap joint with the bearing inner ring of the rear frame, so that the deformation resistance of the cone shell baffle is enhanced; The top outer ring surface of the disc edge baffle plate is opposite to the shoulder inner ring surface of the cone shell baffle plate in front-back direction in the installation state, and a certain distance exists between the top outer ring surface and the shoulder inner ring surface of the cone shell baffle plate in the axial direction.
2. The disc edge cone shell clamping stagnation structure for preventing turbine over rotation of an aeroengine according to claim 1, wherein a certain axial distance is kept between the top outer annular surface of the disc edge baffle and the shoulder inner annular surface of the cone shell baffle without contact friction when the aeroengine works normally; When the low-pressure shaft breaks, the low-pressure turbine rotor component moves backwards, the disc edge baffle moves backwards along with the low-pressure turbine disc, the outer annular surface of the top of the disc edge baffle presses against the inner annular surface of the shoulder of the cone-shell baffle, the first boss is embedded into the second pit to form clamping stagnation, the cone-shell baffle is caused to deform severely, kinetic energy of the low-pressure turbine rotor component is consumed, the rotor is limited to rise, and quick braking is achieved, so that the integrity of the low-pressure turbine component is guaranteed.
3. A disc rim cone shell clamping structure for preventing an aircraft engine turbine from over-rotating as set forth in claim 1 or 2 wherein the top outer annular surface of the disc rim baffle and the shoulder inner annular surface of the cone shell baffle are both conical surfaces, and the cone angle of the top outer annular surface is larger than that of the shoulder inner annular surface, and the higher the backward movement amount of the low pressure turbine rotor component, the tighter the clamping between the top outer annular surface and the shoulder inner annular surface, and the stronger the rotation speed limitation of the low pressure turbine rotor component.
4. A disk edge cone shell clamping stagnation structure for preventing turbine overrunning of an aircraft engine according to claim 1 or 2, wherein the disk edge cone shell clamping stagnation structure is applied to an aircraft engine with a bearing frame behind a last stage turbine rotor.

Description

A dish edge cone shell clamping stagnation structure for preventing aeroengine turbine is changeed Technical Field The invention belongs to the field of aeroengine design, and particularly relates to a disk edge cone shell clamping stagnation structure for preventing an aeroengine turbine from overturning. Background Due to manufacturing and assembly errors, or extreme loads, material defects, etc., the aeroengine may experience shaft breakage failure during operation, which may cause over-rotation of the turbine rotor under high energy gas drive or even rupture of the turbine disc, resulting high energy fragments and possible breakdown of the nacelle and even the aircraft body, with catastrophic consequences. Therefore, it is necessary to perform turbine over-rotation prevention design, and to perform down-rotation on the turbine rotor after the shaft breakage occurs. At present, the turbine of an aeroengine is researched for preventing over-rotation, and most of the turbine is characterized in that the fuel oil supply of a combustion chamber is cut off after a rotating shaft is broken, so that a turbine rotor is lack of high-energy fuel gas driving to decelerate. However, the engine control system still requires a certain time to monitor and determine the event of a shaft breakage and cut off the fuel supply, and the rotational speed of the turbine rotor is rapidly increased in the process. Therefore, the method of actively cutting off oil supply is independently relied on to prevent the rotation speed of the turbine rotor, which is still a very demanding requirement, and it is necessary to design and install an over-rotation protection structure of the turbine rotor, and to rapidly reduce the rotation speed of the turbine rotor after the breakage of the rotating shaft occurs. Disclosure of Invention In order to solve the technical problems, the invention aims to provide a disc edge cone shell clamping structure for preventing an aeroengine turbine from over-rotating, which comprises a disc edge baffle and a cone shell baffle, wherein the disc edge baffle is arranged at the rear side of the turbine disc, the head of the disc edge baffle is provided with a petal-shaped outer ring surface, the cone shell baffle is arranged on an oil cavity bushing, and the shoulder of the cone shell baffle is provided with a petal-shaped inner ring surface. In the mounting state and the normal left-side state of the engine, the outer annular surface of the head part of the disc edge baffle plate is opposite to the front and back of the inner annular surface of the shoulder part of the cone shell baffle plate, and a certain distance is formed between the outer annular surface of the head part of the disc edge baffle plate and the inner annular surface of the shoulder part of the cone shell baffle plate in the axial direction. The invention can limit the rotation speed of the turbine after the rotation shaft of the engine is broken, avoid the catastrophic accident of turbine disc breakage, and simultaneously has the advantages of simple configuration, convenient disassembly and assembly and realization of quick brake. In order to achieve the above purpose, the present invention adopts the following technical scheme: The disc edge cone shell clamping structure for preventing the turbine of the aeroengine from over-rotating comprises a disc edge baffle and a cone shell baffle, wherein the disc edge cone shell clamping structure is arranged at the position of a low-pressure turbine part, limits the rotating speed of the low-pressure turbine rotor part after a low-pressure rotating shaft is broken, and prevents the low-pressure turbine rotor part from over-rotating and the low-pressure turbine disc from breaking; The disc edge baffle is provided with a bottom mounting edge, a head axial end surface and a top outer annular surface, wherein the outer annular surface is provided with a certain taper and is wavy, and first pits and first bosses are uniformly distributed on the outer annular surface at intervals in the circumferential direction; The cone shell baffle is provided with a bottom mounting edge, a head joint edge and a shoulder inner ring surface, wherein the inner ring surface is provided with a certain taper, but smaller than the outer ring surface, the inner ring surface is wavy, and second pits and second bosses are uniformly distributed on the inner ring surface at intervals in the circumferential direction; The disc edge baffle is connected with the turbine disc mounting edge through a second bolt at the position of the bottom mounting edge, so that self fixed mounting is realized; The head joint edge of the cone shell baffle is in lap joint with the bearing inner ring of the rear frame, so that the deformation resistance of the cone shell baffle is enhanced; The top outer ring surface of the disc edge baffle is opposite to the inner ring surface of the shoulder part of the cone shell baffle in front and back in the