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CN-119260344-B - High-temperature component bonding connector decomposition process method

CN119260344BCN 119260344 BCN119260344 BCN 119260344BCN-119260344-B

Abstract

The invention belongs to the technical field of engine connector decomposition, and particularly relates to a bonding connector decomposition process method of a high-temperature component, comprising the following steps of S1, heating a connector by using a heating gun; S2, spraying the prepared loosening agent into the connecting piece after heating for the required heating time, and performing sealing treatment, and S3, after sealing for the required sealing time, decomposing the connecting piece by using decomposing equipment. The connecting pieces are a combustion chamber connecting piece, a high-vortex connecting piece, a low-vortex connecting piece, a nozzle and a turbine rear casing connecting piece, and different loosening agents are selected for different connecting pieces. The method can be used for decomposing the bonding connecting piece of the high-temperature part after the engine works, reduces the labor intensity of workers, improves the quality of the decomposed part, can effectively reduce the problem of higher rejection rate and the like caused by bonding the high-temperature part connecting piece, and can reduce the decomposition time of the high-temperature part connecting piece from original 2h to 0.5h and reduce the repair cost.

Inventors

  • HUANG SONGXUN
  • SUN WENYAN
  • CHEN CHAOGANG

Assignees

  • 中国航发沈阳黎明航空发动机有限责任公司

Dates

Publication Date
20260505
Application Date
20241108

Claims (6)

  1. 1. The process for decomposing the bonding connecting piece of the high-temperature component is characterized by comprising the following steps of: s1, heating a connecting piece by using a heating gun; s2, after heating to the required heating time, spraying the prepared loosening agent and kerosene into the connecting piece and sealing the connecting piece; S3, after the required sealing time is reached, decomposing the connecting piece by using decomposing equipment; The connecting pieces are a combustion chamber connecting piece, a high-vortex connecting piece, a low-vortex connecting piece and a nozzle and turbine rear casing connecting piece; Different connecting pieces are selected from different loosening agents and kerosene; the loosening agent and kerosene are respectively as follows: 20% of combustion chamber connecting pieces, 80% of Littx and 80% of kerosene; High-vortex connecting pieces of HS-190:10%, WD-40:10%, lai Jisi:10%, kerosene 70%; WD-40:15% of low vortex connector; lai Jisi% of kerosene and 80% of kerosene; the jet nozzle and the turbine rear casing connecting piece comprise, by weight, 30% of HS-190, 10% of Lai Jisi, and 60% of kerosene.
  2. 2. The method for decomposing the bonding connection of the high-temperature component according to claim 1, wherein the grease is smeared and sealed within 1min after the prepared loosening agent and kerosene are sprayed.
  3. 3. A method of breaking down a bonded joint of a high temperature component as recited in claim 1, the sealing device is characterized in that the required sealing time is 12h.
  4. 4. The method of claim 1, wherein the heating time is different according to the thermal expansion coefficient of the adjacent parts of the high temperature parts.
  5. 5. A method of breaking down a bonded joint of a high temperature component as recited in claim 1, characterized in that the S1 comprises: the temperature of the heating gun is regulated to 270 ℃ by using the heating gun, and the heating gun is aligned to the connecting piece for heating after reaching 270 ℃.
  6. 6. A method of breaking down a bonded joint of a high temperature component as recited in claim 1, the method is characterized in that the required heating time is 25min.

Description

High-temperature component bonding connector decomposition process method Technical Field The invention belongs to the technical field of engine connector decomposition, and particularly relates to a bonding connector decomposition process method for a high-temperature component. Background After the aeroengine works, the hot end part of the aeroengine bears higher temperature and larger stress, and under the dual effects of temperature and stress, the hot end part connecting piece often has the phenomena of carbon deposition, corrosion and the like, when the aeroengine is decomposed, the end surface connecting pieces of the aeroengine are required to be loosened for subsequent decomposition, but due to the conditions that the connecting piece of the hot end part (a combustion chamber, a turbine assembly and the like) of the aeroengine has more residual carbon deposition, corrosion and the like, the connecting piece of the high-temperature part is not easy to loosen. To solve this problem, a decomposition process method is required to be designed for the connection piece of the high-temperature component. Disclosure of Invention Aiming at the defects existing in the prior art, the invention provides a process for decomposing the bonding connecting piece of the high-temperature component, which can effectively improve the decomposition process of the connecting piece of the high-temperature component, improve the quality of the decomposed part, reduce the decomposition rejection rate and lighten the burden of an operator during decomposition. In order to achieve the above purpose, the following specific technical scheme is adopted: A process method for decomposing a bonding connecting piece of a high-temperature component comprises the following steps: s1, heating a connecting piece by using a heating gun; s2, after heating to the required heating time, spraying the prepared loosening agent and kerosene into the connecting piece and sealing the connecting piece; And S3, after the sealing is carried out for the required sealing time, the connecting piece is decomposed by using decomposing equipment. Further, the connecting piece is a combustion chamber connecting piece, a high-vortex connecting piece, a low-vortex connecting piece and a nozzle and turbine rear casing connecting piece. Furthermore, different connecting pieces select different loosening agents and kerosene. Further, the loosening agent and kerosene are respectively: 20% of combustion chamber connecting pieces, 80% of Littx and 80% of kerosene; High-vortex connecting pieces of HS-190:10%, WD-40:10%, lai Jisi:10%, kerosene 70%; WD-40:15% of low vortex connector; lai Jisi% of kerosene and 80% of kerosene; the jet nozzle and the turbine rear casing connecting piece comprise, by weight, 30% of HS-190, 10% of Lai Jisi, and 60% of kerosene. Further, after spraying the prepared loosening agent and kerosene, grease is smeared and sealed within 1 min. Further, the required sealing time was 12h. Further, the heating time required is different depending on the coefficient of thermal expansion of the adjacent parts of the connection member of the high temperature member. Further, the step S1 includes: the temperature of the heating gun is regulated to 270 ℃ by using the heating gun, and the heating gun is aligned to the connecting piece for heating after reaching 270 ℃. Further, the required heating time was 25min. The invention has the beneficial effects that. The method can be used for decomposing the bonding connecting piece of the high-temperature part after the engine works, reduces the labor intensity of workers, improves the quality of the decomposed part, can effectively reduce the problem of higher rejection rate and the like caused by bonding the high-temperature part connecting piece, and can reduce the decomposition time of the high-temperature part connecting piece from original 2h to 0.5h and reduce the repair cost. Drawings FIG. 1 is a flow chart of a process for decomposing a bonding connection of a high temperature component according to the present invention; FIG. 2 shows a first surface topography of a connecting bolt before spraying a loosening agent in an embodiment; FIG. 3 shows a second surface topography of a connecting bolt prior to spraying a loosening agent in an embodiment; FIG. 4 is a third surface topography of a connecting bolt prior to spraying a loosening agent in an embodiment; FIG. 5 shows a first surface topography of a connecting bolt after spraying a loosening agent in an embodiment; FIG. 6 shows a second surface topography of a connecting bolt after spraying a loosening agent in an embodiment; FIG. 7 shows a third surface topography of a connecting bolt after spraying a loosening agent in an embodiment; FIG. 8 is a cross-sectional view of a connecting bolt after spraying a loosening agent in an embodiment; FIG. 9 is a profile of a longitudinal corrosion layer of a connecting bolt after spraying a loosening agent in an