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CN-121993425-A - Plug component structure is visited in aeroengine hole

CN121993425ACN 121993425 ACN121993425 ACN 121993425ACN-121993425-A

Abstract

The embodiment of the invention provides an aircraft engine hole detection plug assembly structure, and relates to the field of aircraft engines. Aims to solve the problem that the hole detection plug assembly can not simultaneously overcome the uncoordinated deformation of the inner and outer cases and the high-temperature heat circulation working condition. The inner plug comprises an inner plug, an outer plug, a stop ring and a plug piece, wherein an inner plug sealing part at the lower end of the inner plug is connected with an inner-layer casing hole exploring hole mounting seat, an inner plug mounting part at the upper end is assembled in an outer-layer casing hole exploring hole mounting seat, an outer plug sealing part at the lower end of the outer plug is connected with an outer-layer casing hole exploring hole mounting seat, the stop ring is sleeved between an inner plug mounting part at the upper end and an outer plug mounting part at the upper end, and the plug piece is connected with the inner plug mounting part at the upper end. The separate rigid structure and clearance fit are adopted, so that the problem that the hole detection plug assembly fails due to failure after a plurality of high-temperature heat circulation working conditions is solved, and the defect that the plug in a rigid form cannot be adapted to the inner and outer cases due to inconsistent deformation is overcome.

Inventors

  • GAO HAOMAI
  • GU ZHIXIANG
  • QIN WEN

Assignees

  • 中国航发商用航空发动机有限责任公司

Dates

Publication Date
20260508
Application Date
20241106

Claims (9)

  1. 1. The utility model provides an aircraft engine hole surveys end cap subassembly structure for install on outer shell case hole survey hole mount pad and inlayer shell case hole survey hole mount pad, its characterized in that, aircraft engine hole surveys end cap subassembly structure includes: The inner plug is provided with a lower end inner plug sealing part and an upper end inner plug mounting part which are opposite in position, the lower end inner plug sealing part is used for being connected with an inner layer casing hole exploratory hole mounting seat and plugging Kong Tankong of the compressor rectifier, and the upper end inner plug mounting part is assembled in the outer layer casing hole exploratory hole mounting seat; The outer plug is of a central through hole structure, the outer plug is provided with a lower end outer plug sealing part and an upper end outer plug mounting part which are opposite in position, the outer plug is used for being sleeved on the periphery of the inner plug, and the lower end outer plug sealing part is connected with an outer casing hole exploratory hole mounting seat; The stop ring is sleeved between the upper end inner plug mounting part and the upper end outer plug mounting part, the inner periphery of the stop ring is in clearance fit and circumferential limit connection with the upper end inner plug mounting part, and the outer periphery of the stop ring is in clearance fit and circumferential limit connection with the upper end outer plug mounting part; and the blocking piece is connected with the upper end inner blocking installation part and blocks a gap among the upper end inner blocking installation part, the stop ring and the upper end outer blocking installation part.
  2. 2. The aircraft engine hole plug assembly structure of claim 1, wherein: an inner claw is arranged on the inner periphery of the stop ring, and an outer claw is arranged on the outer periphery of the stop ring; An inner plug clamping groove is formed in the periphery of the upper end inner plug mounting part of the inner plug, and an outer plug clamping groove is formed in the periphery of the upper end outer plug mounting part of the outer plug; the inner clamping claw is clamped with the inner plug clamping groove in a clearance fit manner, and the outer clamping claw is clamped with the outer plug clamping groove in a clearance fit manner so as to circumferentially limit the inner plug and the outer plug.
  3. 3. The aircraft engine hole plug assembly structure of claim 2, wherein: The edge of interior end cap draw-in groove sets up the rounding structure, the edge of outer end cap draw-in groove sets up the rounding structure, the root of interior jack catch with the root of outer jack catch all sets up the rounding structure.
  4. 4. An aircraft engine hole plug assembly structure according to any one of claims 1 to 3, wherein: The inner plug sealing part at the lower end of the inner plug comprises a plugging boss, an inner plug thread section and an inner plug sealing edge which are sequentially connected, wherein the plugging boss is used for plugging Kong Tankong of the rectifier of the gas compressor, the inner plug thread section is used for being in threaded connection with the inner layer casing hole exploring mounting seat, and the inner plug sealing edge is used for being in sealing fit with the end face of the inner layer casing hole exploring mounting seat.
  5. 5. The aircraft engine hole plug assembly structure of claim 4, wherein: the end face of the upper end inner plug installation part of the inner plug is provided with a threaded hole, and the threaded hole is used for being in threaded connection with the plugging piece.
  6. 6. An aircraft engine hole plug assembly structure according to any one of claims 1 to 3, wherein: The lower end outer plug sealing part of the outer plug comprises an outer plug thread section and an outer plug sealing edge which are sequentially connected, wherein the outer plug thread section is used for being in threaded connection with the outer casing hole exploring hole mounting seat, and the outer plug sealing edge is used for being in sealing fit with the end face of the outer casing hole exploring hole mounting seat.
  7. 7. The aircraft engine hole plug assembly structure of claim 6, wherein: The outer plug wire locking hole is used for being connected with the casing so as to stop circumferential rotation of the outer plug.
  8. 8. An aircraft engine hole plug assembly structure according to any one of claims 1 to 3, wherein: The upper end inner plug mounting part of the inner plug is of a regular prism structure and is used for being matched with a torque wrench tool, and the upper end inner plug mounting part of the outer plug is of a regular prism structure and is used for being matched with the torque wrench tool.
  9. 9. The aircraft engine hole plug assembly structure of claim 1, wherein: The plugging piece comprises a plugging threaded section and a nut section which are sequentially arranged, wherein the plugging threaded section is in threaded connection with an inner plugging installation part at the upper end of the inner plug, an installation groove is formed in the end face of the nut section and is used for being matched with a torque wrench tool, and a plugging wire locking hole is formed in the periphery of the nut section and is used for being connected with a casing so as to stop the periphery Xiang Zhuaidong of the plugging piece.

Description

Plug component structure is visited in aeroengine hole Technical Field The invention relates to the field of aeroengines, in particular to an aeroengine hole detection plug assembly structure. Background At present, in multistage axial-flow compressors in domestic and foreign aeroengines, a double-layer casing structure is generally adopted for a compressor casing of the next stage, and favorable conditions are provided for radial clearance control. Because the functions of the inner casing and the outer casing are separated, the outer layer mainly transmits load, and the inner layer forms a runner, so that the inner layer runner is prevented from being influenced by large deformation of the outer casing caused by mechanical load or thermal load and the like. Meanwhile, the diameter of the outer-layer casing is larger, the longitudinal rigidity of the casing is improved, and the reliable operation of the engine is facilitated. Because the structural characteristic of the double-layer casing of the air compressor, when the hole detection observation hole is arranged, the hole detection plug structure is required to be matched with the mounting seats of the inner-layer casing and the outer-layer casing at the same time for sealing, so that air leakage is prevented. The common rigid hole detection plug structure cannot adapt to the problem of inconsistent deformation of the inner and outer casing, and the Kong Tan plug component structure adopting the compression spring solves the problem of inconsistent deformation of the inner and outer casing, but the spring is extremely easy to lose elasticity failure after undergoing a plurality of high-temperature thermal cycle working conditions, so that the service life of the Kong Tan plug component is greatly shortened, and the detection and maintenance cost of an engine is increased. Disclosure of Invention The following presents a simplified summary of one or more aspects in order to provide a basic understanding of such aspects. This summary is not an extensive overview of all contemplated aspects, and is intended to neither identify key or critical elements of all aspects nor delineate the scope of any or all aspects. Its sole purpose is to present some concepts of one or more aspects in a simplified form as a prelude to the more detailed description that is presented later. The invention aims to provide an aeroengine hole detection plug assembly structure, which can solve the problems that the hole detection plug assembly cannot simultaneously overcome the deformation incompatibility of an inner casing and an outer casing and the high-temperature heat cycle working condition. Embodiments of the invention may be implemented as follows: The embodiment of the invention provides an aircraft engine hole detection plug assembly structure which is used for being installed on an outer-layer casing hole detection plug installation seat and an inner-layer casing hole detection plug installation seat, wherein the aircraft engine hole detection plug assembly structure comprises an inner plug, an outer plug, a stop ring and a plug piece, the inner plug is provided with a lower end inner plug sealing part and an upper end inner plug installation part, the lower end inner plug sealing part is used for being connected with the inner-layer casing hole detection plug installation seat and blocking Kong Tankong of a compressor rectifier, the upper end inner plug installation part is assembled in the outer-layer casing hole detection hole installation seat, the outer plug is of a central through hole structure, the outer plug is provided with a lower end outer plug sealing part and an upper end outer plug installation part, the lower end outer plug sealing part is connected with the outer-layer casing hole detection plug installation seat, the lower end inner plug sealing part is sleeved between the upper end inner plug installation part and the upper end outer plug installation part, the upper end inner plug sealing part is connected with the upper end outer plug installation part in a circumferential direction, and the upper end sealing part is connected with the upper end sealing part in a gap-circumferential direction, and the upper end sealing part is combined with the upper end sealing part. In addition, the aircraft engine hole detection plug assembly structure provided by the embodiment of the invention can also have the following additional technical characteristics: Optionally, an inner claw is arranged on the inner periphery of the stop ring, and an outer claw is arranged on the outer periphery of the stop ring; an inner plug clamping groove is formed in the periphery of the upper end inner plug mounting part of the inner plug, and an outer plug clamping groove is formed in the periphery of the upper end outer plug mounting part of the outer plug; the inner clamping claw is clamped with the inner plug clamping groove in a clearance fit manner, and the outer clamping claw