CN-116398248-B - Disk edge damping ring brake structure for preventing turbine of aero-engine from flying

CN116398248BCN 116398248 BCN116398248 BCN 116398248BCN-116398248-B

Abstract

The invention provides a disc edge damping ring brake structure for preventing a turbine of an aeroengine from flying, which comprises a disc edge baffle, a wedge-shaped cone shell and a damping ring, wherein the disc edge baffle is arranged at the rear side of the turbine disc, the wedge-shaped cone shell is arranged on a rear frame of the turbine, and the damping ring is welded on the wedge-shaped cone shell. In the installation state and the normal working state of the engine, the wedge-shaped ring surface of the shoulder part of the disc edge baffle plate is opposite to the front side and the rear side of the wedge-shaped inner ring surface of the damping ring, a certain gap exists between the wedge-shaped ring surface and the wedge-shaped inner ring surface of the damping ring, once a rotating shaft fracture fault occurs, the turbine rotor moves backwards, the wedge-shaped ring surface of the disc edge baffle plate contacts and rubs with the wedge-shaped ring surface of the damping ring, kinetic energy of the turbine rotor is consumed, the rotating speed of the turbine rotor is limited, rapid braking is realized, and the integrity of the turbine rotor and the safety of the engine are ensured.

Inventors

HONG JIE
ZHANG JIAN
GUO HAILONG
LI CHAO
MA YANHONG

Assignees

北京航空航天大学
中国航发湖南动力机械研究所

Dates

Publication Date: 20260505
Application Date: 20230404

Claims (3)

1. The disk edge damping ring brake structure for preventing the turbine of the aeroengine from flying is characterized by comprising a disk edge baffle, a wedge-shaped conical shell and a damping ring, wherein the disk edge damping ring brake structure is arranged at the position of a low-pressure turbine component, limits the rotating speed of the low-pressure turbine rotor component after a low-pressure rotating shaft is broken, and avoids the over-rotation of the low-pressure turbine rotor component and the breakage of a low-pressure turbine disk; the disk edge baffle is provided with a bottom mounting edge, a head flange and a shoulder wedge-shaped ring surface, the wedge-shaped cone shell is provided with a bottom mounting edge, a head joint edge and an overhanging shell, and the damping ring is provided with a wedge-shaped outer ring surface and a wedge-shaped inner ring surface; the disk edge baffle is axially pressed with the rear end surface of the joggle structure at the position of the head baffle edge to limit the axial displacement of the low-pressure turbine blade; The head joint edge of the wedge-shaped cone shell is also in lap joint with the front end of the inner ring of the flow director, so that the deformation resistance of the wedge-shaped cone shell is enhanced; the damping ring is welded on the overhanging shell of the wedge-shaped conical shell through the wedge-shaped outer ring surface; the shoulder wedge-shaped annular surface of the disc edge baffle plate and the wedge-shaped inner annular surface of the damping ring are opposite in front-back direction in the installation state, a certain gap exists between the shoulder wedge-shaped annular surface and the wedge-shaped inner annular surface, and the distance between the two wedge-shaped annular surfaces is adjusted by modifying the geometric dimension of the wedge-shaped conical shell and the thickness of the damping ring; When the aeroengine works normally, a certain gap is kept between the wedge-shaped annular surface of the shoulder part of the disc edge baffle plate and the wedge-shaped inner annular surface of the damping ring, and contact friction is avoided; 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 shoulder wedge-shaped annular surface is pressed towards the wedge-shaped inner annular surface, contact friction occurs between the low-pressure turbine rotor component and the shoulder wedge-shaped annular surface, kinetic energy of the low-pressure turbine rotor component is consumed, the rotating speed of the low-pressure turbine rotor component is limited to rise, and rapid braking is achieved, so that the integrity of the low-pressure turbine component is guaranteed.
2. A disk rim damping ring brake structure for preventing turbine spin of an aircraft engine as set forth in claim 1, wherein the disk rim damping ring brake structure is applied to an aircraft engine having a load bearing frame behind a last stage turbine rotor.
3. A disc rim damping ring brake structure for preventing turbine spin of an aircraft engine according to claim 1, wherein the damping ring is made of metal rubber material, and the metal rubber is a homogeneous elastic porous material made of metal wires.

Description

Disk edge damping ring brake structure for preventing turbine of aero-engine from flying Technical Field The invention belongs to the field of aeroengine design, and particularly relates to a disk edge damping ring brake structure for preventing a turbine of an aeroengine from flying. Background The aero-engine may cause broken shaft failure during operation due to extreme loads, high cycle fatigue, corrosion, material defects, manufacturing and assembly errors, or other collateral events. After the rotating shaft is broken, the turbine rotor is driven by high-energy fuel gas to rise, if the speed is increased to a certain extent, the turbine disc is broken due to overlarge centrifugal stress, and high-energy fragments generated by the turbine disc are likely to break down the engine casing and even the aircraft body, so that disastrous results are caused. Therefore, the design of the turbine rotor over-rotation protection structure and the prevention of turbine over-rotation after the occurrence of the shaft breakage are indispensable matters in the design and development processes of the aero-engine. Aircraft engines typically monitor rotor speed by installing sensors and once a shaft break and turbine disk overrun problem is found, the fuel supply to the combustion chamber is cut off and the turbine rotor is decelerated by the lack of high energy gas drive. However, the engine control system still needs a certain time for monitoring and judging the breaking event of the rotating shaft and cutting off the oil supply, the rotating speed of the turbine rotor is rapidly increased in the process, and the rotating speed of the turbine is limited by the control system independently after the rotating shaft fails, so that the requirement is still very strict. Therefore, it is necessary to design and install a turbine rotor over-rotation protection structure to prevent turbine over-rotation after a shaft breakage occurs. Disclosure of Invention In order to solve the technical problems, the invention aims to provide the disk edge damping ring brake structure for preventing the turbine of the aeroengine from flying, which can limit the rotation speed of the turbine after the broken shaft of the engine fails, avoid catastrophic accidents of turbine disk rupture and has the advantages of simple configuration and convenient disassembly and assembly. In order to achieve the above purpose, the present invention adopts the following technical scheme: The disk edge damping ring brake structure for preventing the turbine of the aeroengine from flying comprises a disk edge baffle, a wedge-shaped conical shell and a damping ring, wherein the disk edge damping ring brake structure is arranged at the position of a low-pressure turbine component, limits the rotating speed of the low-pressure turbine rotor component after a low-pressure rotating shaft is broken, and prevents the low-pressure turbine rotor component from over-rotating and the low-pressure turbine disk from being broken; the disk edge baffle is provided with a bottom mounting edge, a head flange and a shoulder wedge-shaped ring surface, the wedge-shaped cone shell is provided with a bottom mounting edge, a head joint edge and an overhanging shell, and the damping ring is provided with a wedge-shaped outer ring surface and a wedge-shaped inner ring surface; the disk edge baffle is axially pressed with the rear end surface of the joggle structure at the position of the head baffle edge to limit the axial displacement of the low-pressure turbine blade; the head joint edge of the wedge-shaped cone shell is also in joint with the front end of the flow director, so that the deformation resistance of the wedge-shaped cone shell is enhanced; the damping ring is welded on the overhanging shell of the wedge-shaped conical shell through the wedge-shaped outer ring surface; The shoulder wedge-shaped annular surface of the disc edge baffle plate and the wedge-shaped inner annular surface of the damping ring are opposite in front-back direction in the installation state, a certain gap exists between the shoulder wedge-shaped annular surface and the wedge-shaped inner annular surface of the damping ring, and the distance between the two wedge-shaped annular surfaces is adjusted by modifying the geometric dimension of the wedge-shaped conical shell and the thickness of the damping ring. Further, when the aeroengine works normally, a certain gap is kept between the wedge-shaped annular surface of the shoulder part of the disc edge baffle plate and the wedge-shaped inner annular surface of the damping ring, and contact friction does not occur; 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 shoulder wedge-shaped annular surface is pressed towards the wedge-shaped inner annular surface, contact friction occurs between the low-pressure turbine rotor compone