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CN-121976880-A - Quick-release structure of plug of aircraft engine hole detector

CN121976880ACN 121976880 ACN121976880 ACN 121976880ACN-121976880-A

Abstract

The application belongs to the field of aeroengine hole probes, and particularly relates to a quick-release structure of an aeroengine hole probe plug. The structure comprises a plug, a spring, a mounting seat, a plug cover and a rubber ring. According to the quick-release structure of the plug of the aircraft engine hole detector, the ball cone centering matching structure is arranged on the plug and the plug cover, so that the plug and the plug cover or the mounting seat slide after the installation, the self-sealing of a hole detection channel is realized by utilizing the rubber ring sealing structure, the contact abrasion between the plug and the plug cover or the mounting seat is avoided, the problem that compressed gas leaks through a gap of the hole detection channel in a flow channel is solved, and the loss of gas compression efficiency is reduced.

Inventors

  • BAI YONGQIU
  • Jia duo
  • LIU BO

Assignees

  • 中国航发沈阳发动机研究所

Dates

Publication Date
20260505
Application Date
20260210

Claims (7)

  1. 1. The utility model provides an aeroengine hole appearance end cap quick detach structure which characterized in that includes: The mounting seat (3), the mounting seat (3) is mounted on the casing, an external thread is arranged on the outer ring surface of the mounting seat (3), a ladder-shaped cavity is arranged inside the mounting seat, and the ladder-shaped cavity comprises an upper cavity and a lower cavity; the blanking cover (4), an inner ring surface of the blanking cover (4) is provided with an inner thread which is mutually matched with the mounting seat (3), the outer end surface of the blanking cover (4) is provided with a strip-shaped opening, and a blanking cover inner conical surface transition section is arranged between the inner thread and the strip-shaped opening; the plug (1) comprises an eccentric positioning section and a guide rod, wherein the eccentric positioning section is provided with an eccentric spherical surface (11) which is mutually matched with the inner conical surface transition section of the plug cover, the end part of the eccentric positioning section is provided with a square table (13) which is mutually matched with the strip-shaped opening, the square table (13) is provided with an internal threaded hole (14) which is mutually matched with the plug dismounting tool of the hole detector, and the guide rod is provided with an annular groove (12); the spring (2) is arranged in the upper cavity, is coaxially sleeved on the guide rod, and performs centering limit on the eccentric spherical surface (11) and the inner conical surface transition section of the plug cover through the pretightening force of the spring (2); the rubber ring (5), the rubber ring (5) is installed in the annular groove (12), and the rubber ring (5) generates elastic compression deformation between the lower cavity and the annular groove (12) to form a sealing pair.
  2. 2. The quick release structure of an aircraft engine hole probe plug according to claim 1, wherein the mounting seat (3) and the casing are connected into a whole through a bolt fixing mode.
  3. 3. The quick release structure of an aircraft engine hole probe plug according to claim 1, wherein the mounting seat (3) and the casing are integrally connected by welding.
  4. 4. The quick-release structure of the aircraft engine hole detector plug according to claim 1, wherein the installation seat (3) and the plug cover (4) are provided with mutually-matched wire locking holes, and the plug cover (4) is prevented from being loosened with the installation seat (3) through wire locking after being installed.
  5. 5. The quick-release structure of the aircraft engine hole probe plug according to claim 4, wherein positioning score lines are arranged on two sides of the strip-shaped opening of the plug cover (4).
  6. 6. The quick release structure of an aircraft engine hole probe plug according to claim 5, wherein a positioning score line is arranged on a square table (13) of the eccentric positioning section.
  7. 7. The quick release structure of an aircraft engine hole probe plug according to claim 6, wherein the guide rod is in clearance fit with the lower cavity of the mounting seat (3).

Description

Quick-release structure of plug of aircraft engine hole detector Technical Field The application belongs to the field of aeroengine hole probes, and particularly relates to a quick-release structure of an aeroengine hole probe plug. Background The surface state of the runner piece can be checked regularly in the whole service life period of the aeroengine so as to prevent the problems that the use safety of the engine is affected due to exceeding of cracks, falling blocks and the like of the runner piece. The flow passage member is usually inspected by visual or hole detection equipment, and the flow passage members such as the rest rotor, the combustion chamber and the like are inspected by the hole detection equipment, wherein the flow passage member is usually positioned at an inlet and an outlet of an engine (such as an inlet casing support plate, a primary fan rotor inlet side or a turbine rotor exhaust side) and can be inspected visually. The hole detector is a common instrument and equipment in the field of aeroengines, and can detect or inspect the interior of the engine on the basis of not disassembling or damaging the engine structure. The existing hole detector plug mainly prevents the plug from popping up through a plane contacted between the plug and the hole detector seat. The prior hole detector plugging structure has no effective centering limit structure under the alternating actions of engine vibration, pressure of compressed gas in a runner and the like along with the increase of the service time of an engine, the contact plane of a plug and a plugging cover or a mounting seat can be repeatedly contacted and rubbed, so that the plug is slightly worn, the surface wear of the plug is overlarge, metal scraps generated after wear enter a rotating groove of the plugging cover, the plug is difficult to assemble and disassemble, the smooth development of external field guarantee work is influenced, and meanwhile, the prior hole detector plugging structure is not provided with an effective sealing structure, the compressed gas in the runner can leak out through gaps between hole detection channels, and the compression efficiency is lost. Accordingly, there is a need for a solution that overcomes or mitigates at least one of the above-mentioned drawbacks of the prior art. Disclosure of Invention The application aims to provide a quick-release structure of an aircraft engine hole probe plug, which aims to solve at least one problem in the prior art. The technical scheme of the application is as follows: an aircraft engine hole finder end cap quick detach structure includes: the mounting seat is mounted on the casing, external threads are arranged on the outer ring surface of the mounting seat, a stepped cavity is arranged in the mounting seat, and the stepped cavity comprises an upper cavity and a lower cavity; The inner ring surface of the blanking cover is provided with internal threads which are mutually matched with the mounting seat, the outer end surface of the blanking cover is provided with a strip-shaped opening, and a blanking cover inner conical surface transition section is arranged between the internal threads and the strip-shaped opening; the plug comprises an eccentric positioning section and a guide rod, wherein the eccentric positioning section is provided with an eccentric spherical surface which is mutually matched with the inner conical surface transition section of the plug cover, the end part of the eccentric positioning section is provided with a square table which is mutually matched with the strip-shaped opening, and the square table is provided with an internal threaded hole which is mutually matched with the plug dismounting tool of the hole detector; The spring is arranged in the upper cavity, is coaxially sleeved on the guide rod, and performs centering limit on the eccentric spherical surface and the inner conical surface transition section of the blanking cover through the pretightening force of the spring; The rubber ring is arranged in the annular groove, and elastic compression deformation is generated between the lower cavity and the annular groove to form a sealing pair. In at least one embodiment of the present application, the mounting base and the casing are integrally connected by a bolt fastening manner. In at least one embodiment of the present application, the mounting base and the casing are integrally connected by welding. In at least one embodiment of the application, the mounting seat and the plugging cover are provided with mutually matched wire locking holes, and the plugging cover is prevented from loosening with the mounting seat through wire locking after being mounted. In at least one embodiment of the application, positioning score lines are arranged on two sides of the strip-shaped opening of the blanking cover. In at least one embodiment of the present application, positioning score lines are provided on four sides of the eccentric positioning