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CN-122014679-A - Casing assembly with containing capability and engine

CN122014679ACN 122014679 ACN122014679 ACN 122014679ACN-122014679-A

Abstract

The invention provides a casing assembly with containing capacity and an engine, wherein the casing assembly comprises a casing, stator blades arranged in an inner cavity of the casing, a plurality of stator blade rings are arranged along the circumferential direction of the casing assembly, the stator blade rings are arranged along the axial direction of the casing assembly, rotor blade rings are arranged between adjacent stator blade rings and comprise a plurality of rotor blades arranged along the circumferential direction of the rotor blade rings, a honeycomb structure is arranged on the circumferential part of the casing, and at least part of the honeycomb structure corresponds to the rotor blades along the radial direction. Therefore, if the engine is abnormal in the running process, and the rotor blade flies off due to factors such as fracture, the flying off rotor blade can strike the position of the casing where the honeycomb structure is arranged, and the honeycomb structure can greatly absorb the flying off energy of the rotor blade, so that the containing capacity of the casing assembly is greatly enhanced, the rotor blade is prevented from flying out of the casing, the safety performance of the engine is improved, and the flight safety is ensured.

Inventors

  • SUN HUIMIN
  • CHEN WEI
  • Si Wulin
  • FENG JINZHANG

Assignees

  • 中国航发商用航空发动机有限责任公司

Dates

Publication Date
20260512
Application Date
20241112

Claims (11)

  1. 1. A casing assembly (10) having containment capability, comprising: A casing (110); A plurality of stator blades (120) are arranged in the inner cavity of the casing (110), the stator blades (120) are arranged into stator blade rings along the circumferential direction of the casing assembly (10), the stator blade rings are arranged along the axial direction (X) of the casing assembly (10), rotor blade rings are arranged between adjacent stator blade rings, and the rotor blade rings comprise a plurality of rotor blades (200) arranged along the circumferential direction of the rotor blade rings; And a honeycomb structure (130) provided on the periphery of the casing (110), wherein at least part of the honeycomb structure (130) corresponds to the rotor blade (200) in the radial direction (Y) of the casing assembly (10).
  2. 2. The receiver assembly (10) of claim 1, wherein the honeycomb structure (130) is offset from the stator blades (120) in the radial direction (Y).
  3. 3. The casing assembly (10) according to claim 2, wherein one portion of the honeycomb structure (130) corresponds to a gap between the stator blade (120) and the rotor blade (200) in the radial direction (Y), and another portion corresponds to the rotor blade (200) in the radial direction (Y).
  4. 4. The casing assembly (10) according to claim 1, wherein the honeycomb structure (130) is disposed in a position corresponding to a rotor blade (200) of a first stage, the rotor blade (200) of the first stage being a rotor blade (200) of a plurality of rotor blade rings proximate a fan disk mounting side.
  5. 5. A casing assembly (10) according to claim 3, wherein the casing (110) comprises an inner wall (111) and an outer wall (112), the inner wall (111) enclosing the inner cavity in which the stator blades (120) are arranged, the outer wall (112) surrounding the inner wall (111) and enclosing a receiving cavity (113) with the inner wall (111), The honeycomb structure (130) is arranged in the accommodating cavity (113).
  6. 6. The casing assembly (10) according to claim 5, characterized in that the surface of the inner wall (111) facing the housing cavity (113) is provided with first positioning ribs (114), the first positioning ribs (114) being arranged in pairs along the axial direction (X), One of the first positioning ribs (114) arranged in pairs is arranged at a position corresponding to a gap between the stator blade (120) and the rotor blade (200) along the radial direction (Y), the other is arranged at a position corresponding to the rotor blade (200) along the radial direction (Y), and mounting grooves for accommodating the honeycomb structure (130) are formed between the first positioning ribs (114) arranged in pairs.
  7. 7. The receiver assembly (10) of claim 6, wherein the honeycomb structure (130) is disposed in plurality along the axial direction (X), and the first positioning ribs (114) are disposed in plurality of pairs along the axial direction (X).
  8. 8. The receiver assembly (10) of claim 5, wherein the honeycomb structure (130) is disposed against the inner wall (111) and spaced from the outer wall (112).
  9. 9. The receiver assembly (10) of claim 1, wherein the stator vane (120) is an aluminum-based composite.
  10. 10. The receiver assembly (10) of claim 1, wherein the honeycomb structure (130) includes a honeycomb layer (131), a satin layer (132), and a resin base layer (133); and a plurality of satin fabric layers (132) are paved on two opposite end surfaces of the honeycomb layer (131), and a resin base layer (133) is arranged between the adjacent satin fabric layers (132).
  11. 11. An engine, comprising: the receiver assembly (10) of any one of claims 1-9; and a rotor blade ring provided between adjacent stator blade rings, the rotor blade ring including a plurality of rotor blades (200) provided along a circumferential direction of the casing assembly (10), at least a portion of the honeycomb structure (130) corresponding to the rotor blades (200) along the radial direction (Y).

Description

Casing assembly with containing capability and engine Technical Field The invention relates to the field of aeroengines, in particular to a casing assembly with containing capacity and an engine. Background The aeroengine is a highly complex and precise thermodynamic machine, and as the heart of an airplane, not only is the power of the airplane in flight, but also is an important thrust for promoting the development of aviation industry, and each important revolution in the human aviation history is indistinguishable from the technical progress of the aeroengine. In the related art, the casing has the problem of insufficient containing capacity, and in extreme cases, rotor blades can be led to fly out of the casing to influence the safety performance of the engine. Disclosure of Invention The present invention has been made to solve the above-mentioned problems, and an object of the present invention is to provide a casing assembly and an engine having a casing capacity, which can improve the casing capacity. The application discloses a casing assembly with containing capacity, which comprises a casing, stator blades arranged in an inner cavity of the casing, a plurality of stator blade rings arranged along the circumferential direction of the casing assembly, a plurality of stator blade rings arranged along the axial direction of the casing assembly, rotor blade rings arranged between adjacent stator blade rings, and a honeycomb structure arranged on the circumferential portion of the casing, wherein the rotor blade rings comprise a plurality of rotor blades arranged along the circumferential direction of the rotor blade rings, and at least part of the honeycomb structure corresponds to the rotor blades along the radial direction. Therefore, if the engine is abnormal in the running process, and the rotor blade flies off due to factors such as fracture, the flying off rotor blade can strike the position of the casing where the honeycomb structure is arranged, and the honeycomb structure can greatly absorb the flying off energy of the rotor blade, so that the containing capacity of the casing assembly is greatly enhanced, the rotor blade is prevented from flying out of the casing, the safety performance of the engine is improved, and the flight safety is ensured. Optionally, the honeycomb structure is offset from the stator vanes in the radial direction. In this way, in the first aspect, the honeycomb structure material can be saved, the material cost can be reduced, and in the second aspect, the space required for accommodating the honeycomb structure can be reduced, and the compactness of the casing assembly can be improved. Optionally, a portion of the honeycomb structure corresponds to a gap between the stator blade and the rotor blade in the radial direction, and another portion corresponds to the rotor blade in the radial direction. In this way, on the one hand, the position of the casing possibly being impacted when the rotor blade flies off can be covered as much as possible, so that the safety performance is improved, and on the second hand, the material waste caused by the arrangement of the honeycomb structure at the corresponding position of the stator blade is avoided. Optionally, the honeycomb structure is disposed at a position corresponding to a rotor blade of the first stage, and the rotor blade of the first stage is a rotor blade of the plurality of rotor blade rings near a mounting side of the fan disk. In the working process, the rotor blade of the first stage is most prone to flying off, and kinetic energy generated during flying off is large, so that the honeycomb structure is arranged at the position, and reliable safety guarantee is provided. Optionally, the casing includes inner wall and outer wall, the inner wall encloses into the setting stator blade the inner chamber, the outer wall is around the inner wall, and encloses into the accommodation chamber with the inner wall, honeycomb locates in the accommodation chamber. In this way, the wall shell of the casing forms a hollowed-out structure, so that the honeycomb structure is arranged conveniently, the structural compactness is improved, in the second aspect, the mask protection can be provided for the honeycomb structure, and in the third aspect, the structure is light-weighted. Optionally, the surface of the inner wall facing the accommodating cavity is provided with first positioning ribs, the first positioning ribs are arranged in pairs along the axial direction, the arrangement position of one of the first positioning ribs in pairs corresponds to the gap between the stator blade and the rotor blade along the radial direction, the arrangement position of the other one of the first positioning ribs corresponds to the rotor blade along the radial direction, and a mounting groove for accommodating the honeycomb structure is formed between the first positioning ribs arranged in pairs. The arrangement mode can improve the structur