Usage method of a tooling for repairing the flow channel of an axial casing of an aeroengine

Abstract

The present invention relates to a method for using a tool for repairing the flow passage of an axial flow casing of an aero-engine. The tool for repairing the flow passage of the axial flow casing of the aero-engine includes a first protective ring adapted to the second-stage stator vane mounting groove, a second protective ring adapted to the third-stage stator vane mounting groove, a spigot protective ring, and a plurality of plugs adapted to the stator vane mounting holes. The outer wall of the first protective ring is in small-clearance fit with the inner wall of the second-stage stator vane mounting groove, the outer wall of the second protective ring is in small-clearance fit with the inner wall of the third-stage stator vane mounting groove, the spigot protective ring is sleeved on the left-end spigot of the axial flow casing. During assembly, between the first protective ring and the inner wall of the second-stage stator vane mounting groove and between the second protective ring and the inner wall of the third-stage stator vane mounting groove are adhesively fixed with glue, and the plugs and the stator vane mounting holes are adhesively fixed with glue.

Description

Technical Field

[0001] The present invention relates to the technical field of auxiliary equipment for repairing aero - engines, in particular to a method for using a tool for repairing the flow passage of an axial - flow casing of an aero - engine. Background Technique

[0002] The axial - flow casing of a certain type of aero - engine is of a split - type structure, and the blank is made of an integral casting. Its structure is as Figure 1 shown. After installation, a first inner flow passage 1, a second inner flow passage 2, a third inner flow passage 3, and a fourth inner flow passage 5 with different inner diameters are formed. Among them, a plurality of stator blade mounting holes 10 are circumferentially arranged on the upper edge of the second inner flow passage 2. A T - shaped second - stage stator blade mounting groove 4 is formed between the third inner flow passage 3 and the fourth inner flow passage 5. A T - shaped third - stage stator blade mounting groove 7 is formed between the fourth inner flow passage 5 and the tail - side end 6. And Al - Si coatings are applied to the inner walls of the first inner flow passage 1, the third inner flow passage 3, and the fourth inner flow passage 5. When machining the inner flow passage of the above - mentioned aero - engine axial - flow casing, a set of data points is used for control and the numerical control turning method is adopted. Whether the processed size is accurate is particularly important for controlling the performance parameters of the compressor. In actual processing, due to factors such as machining operation errors and deformation of thin - wall parts, the inner flow passage is out - of - tolerance. After scanning and measuring the flow passage of the casing assembly, it is found that the overall size of the flow passage deviates outward from the theoretical value by about 0.15 - 0.20 mm, and the overall flow passage expands outward from the theoretical value, which greatly affects the performance parameters of the compressor. Summary of the Invention

[0003] The technical problem to be solved by the present invention is to provide a tool for repairing the flow passage of an aero - engine axial - flow casing that is easy to assemble and convenient to operate, and its using method.

[0004] To solve the above - mentioned technical problem, the tool for repairing the flow passage of an aero - engine axial - flow casing provided by the present invention includes a first protective ring adapted to the second - stage stator blade mounting groove, a second protective ring adapted to the third - stage stator blade mounting groove, a spigot protective ring, and a plurality of plugs adapted to the stator blade mounting holes. The outer wall of the first protective ring has a small - clearance fit with the inner wall of the second - stage stator blade mounting groove. The outer wall of the second protective ring has a small - clearance fit with the inner wall of the third - stage stator blade mounting groove. The spigot protective ring is sleeved on the left - end spigot of the axial - flow casing. During assembly, glue is used to adhesively fix the first protective ring and the inner wall of the second - stage stator blade mounting groove, and the second protective ring and the inner wall of the third - stage stator blade mounting groove. The plugs and the stator blade mounting holes are adhesively fixed with glue.

[0005] Furthermore, the first protective ring is composed of two first half - ring bodies of the same structure spliced together, and the second protective ring is composed of two second half - ring bodies of the same structure spliced together.

[0006] Furthermore, the first half - ring body, the second half - ring body, the plugs, and the spigot protective ring are obtained by turning aluminum alloy.

[0007] The usage method of the tooling for repairing the flow passage of the axial-flow casing of an aero-engine includes the following steps. First, insert two first half-rings into the second-stage stator vane installation groove, and apply glue between the first half-ring and the second-stage stator vane installation groove. The first half-rings form the first protection ring. Insert two second half-rings into the third-stage stator vane installation groove, and apply glue between the second half-ring and the third-stage stator vane installation groove. The second half-rings form the second protection ring. Each plug is bonded to the stator vane installation hole with glue to close the stator vane installation hole. Fix the spigot protection ring at the left-end spigot of the axial-flow casing. Remove the Al-Si coating on the inner walls of the first inner flow passage, the third inner flow passage, and the fourth inner flow passage until the metal matrix is exposed. Carry out sandblasting treatment on the metal processing surface to be sprayed, reduce the surface roughness, and then carry out secondary overall spraying of the flow passage. Then, reprocess the first inner flow passage, the third inner flow passage, and the fourth inner flow passage by using the numerical control machining method to ensure the flow passage size requirements. Through the protection of the tooling for repairing the casing flow passage, combined with the overall spraying process, the reprocessing of the oversized inner flow passage size of the axial-flow casing is carried out.

[0008] Technical effects of the invention: (1) The tooling for repairing the flow passage of the axial-flow casing of the aero-engine of the present invention ensures the feasibility of the overall secondary spraying repair scheme of the coating in the casing compared with the prior art, protects the precision dimensions from being damaged, and greatly improves the spraying efficiency at the same time. The first protection ring and the second protection ring are obtained by combining half-rings, which are easy to assemble. (2) The first protection ring, the second protection ring, and the plugs are all fixed by gluing with glue, which is convenient for subsequent disassembly. (3) The first half-ring, the second half-ring, the plugs, and the spigot protection ring are made of aluminum alloy material, which can prevent the parts from being bruised. Brief Description of the Drawings

[0009] The present invention will be further described in detail below with reference to the accompanying drawings of the specification:

[0010] Figure 1 is a schematic cross-sectional structure diagram of the flow passage of the axial-flow casing of an aero-engine;

[0011] Figure 2 is a schematic cross-sectional structure diagram after the tooling for repairing the flow passage of the axial-flow casing of the present invention is assembled;

[0012] In the figure:

[0013] The first inner flow passage 1, the second inner flow passage 2, the third inner flow passage 3, the second-stage stator vane installation groove 4, the fourth inner flow passage 5, the tail side end 6, the third-stage stator vane installation groove 7, the left-end spigot 8, the threaded hole 9, the stator vane installation hole 10, the spigot protection ring 11, the first protection ring 12, the second protection ring 13, the plug 14, the bolt 15, the axial-flow casing 16. Detailed Embodiment

[0014] Embodiment 1

[0015] As shown Figures 1 to 2 in the figure, the tool for repairing the axial flow casing flow path of the aero-engine in this embodiment includes a first protection ring 12 adapted to the second-stage stator vane installation groove 4, a second protection ring 13 adapted to the third-stage stator vane installation groove 7, a spigot protection ring 11, and 30 plugs 14 adapted to the stator vane installation holes 10. The first protection ring 12 is composed of two first semi-ring bodies spliced together, and the second protection ring 13 is composed of two second semi-ring bodies spliced together; the outer wall of the first protection ring 12 is in small clearance fit with the inner wall of the second-stage stator vane installation groove 4, and the clearance is less than 2.0 mm. The outer wall of the second protection ring 13 is in small clearance fit with the inner wall of the third-stage stator vane installation groove 7, and the clearance is less than 2.0 mm. The spigot protection ring 11 is sleeved on the left-end spigot 8 of the axial flow casing 16. A flange is provided on the periphery of the left-end spigot 8, and threaded holes 9 are provided on the flange. The structure of the spigot protection ring 11 includes an integrally formed inner ring platform and outer ring platform. An inner groove nested with the left-end spigot 8 is formed between the inner ring platform and the outer ring platform. Mounting holes are provided on the outer ring platform. When the spigot protection ring 11 is installed, the inner ring platform is placed inside the left-end spigot 8, and the outer ring platform is placed outside the left-end spigot 8. The spigot protection ring 11 is fixed by the cooperation of bolts 15, mounting holes, and threaded holes. Moreover, the space between the first protection ring 12 and the inner wall of the second-stage stator vane installation groove 4, and the space between the second protection ring 13 and the inner wall of the third-stage stator vane installation groove 7 are filled and glued with glue. The plugs 14 and the stator vane installation holes 10 are filled and glued with glue. The glue selected is 703 glue.

[0016] Preferably, the first semi-ring body, the second semi-ring body, the plugs 14, and the spigot protection ring 11 are obtained by turning aluminum alloy.

[0017] Embodiment 2

[0018] Usage method of the tool for repairing the flow passage of the axial casing of an aeroengine, including the following steps: First, insert two first half rings into the second-stage stator vane installation groove 4, and apply 703 glue between the first half ring and the second-stage stator vane installation groove 4. The first half rings form a circular first protection ring 12. Insert two second half rings into the third-stage stator vane installation groove 7, and apply 703 glue between the second half ring and the third-stage stator vane installation groove 7. The second half rings form a circular second protection ring. The gap between the outer wall of the second protection ring 13 and the inner wall of the third-stage stator vane installation groove 7 and the gap between the outer wall of the first protection ring 12 and the inner wall of the second-stage stator vane installation groove 4 are both less than 2.0 mm. Each plug 14 is bonded to the stator vane installation hole 10 with 703 glue to close the stator vane installation hole 10. Fix the spigot protection ring 11 to the left-end spigot 8 of the axial casing 16 with bolts 15. Remove the Al-Si coating on the inner walls of the first inner flow passage 1, the third inner flow passage 3, and the fourth inner flow passage 5 until the metal matrix is exposed. Perform sandblasting on the metal processing surface to be sprayed to reduce the surface roughness, and then perform secondary overall spraying on the flow passage. Then, reprocess the first inner flow passage 1, the third inner flow passage 3, and the fourth inner flow passage 5 by using the numerical control processing method to ensure the flow passage size requirements. Through the protection of the tool for repairing the casing flow passage, combined with the overall spraying process, the reprocessing of the over-tolerance of the inner flow passage size of the axial casing is carried out.

[0019] Obviously, the above embodiments are only examples for clearly illustrating the present invention, rather than limiting the implementation manners of the present invention. For those of ordinary skill in the art, other different forms of changes or variations can be made based on the above description. It is not necessary and impossible to list all the implementation manners here. And these obvious changes or variations derived from the spirit of the present invention are still within the protection scope of the present invention.

Claims

1. A method of using a tool for repairing the flow path of an axial casing of an aeroengine, characterized in that, The tooling for repairing the flow path of the axial casing of an aero-engine includes a first protective ring adapted to the second-stage stator blade mounting groove, a second protective ring adapted to the third-stage stator blade mounting groove, a spigot protective ring, and a plurality of plugs adapted to the stator blade mounting holes. The outer wall of the first protective ring is in small-clearance fit with the inner wall of the second-stage stator blade mounting groove. The outer wall of the second protective ring is in small-clearance fit with the inner wall of the third-stage stator blade mounting groove. The spigot protective ring is sleeved on the left-end spigot of the axial casing. During assembly, the first protective ring and the inner wall of the second-stage stator blade mounting groove, and the second protective ring and the inner wall of the third-stage stator blade mounting groove are adhesively fixed with glue. The plugs and the stator blade mounting holes are adhesively fixed with glue. The first protective ring is composed of two first half-ring bodies of the same structure spliced together. The second protective ring is composed of two second half-ring bodies of the same structure spliced together. The usage method of the tooling for repairing the flow path of the axial casing of an aero-engine includes the following steps. First, the two first half-ring bodies are snapped into the second-stage stator blade mounting groove, and glue is applied between the first half-ring bodies and the second-stage stator blade mounting groove. The first half-ring bodies form the first protective ring. The two second half-ring bodies are snapped into the third-stage stator blade mounting groove, and glue is applied between the second half-ring bodies and the third-stage stator blade mounting groove. The second half-ring bodies form the second protective ring. Each plug is adhesively bonded to the stator blade mounting hole to close the stator blade mounting hole. The spigot protective ring is fixed on the left-end spigot of the axial casing. The Al-Si coating applied to the inner walls of the first inner flow path, the third inner flow path, and the fourth inner flow path is removed until the metal matrix is exposed. The metal processing surface to be sprayed is sandblasted to reduce the surface roughness, and then the flow path is spray-coated integrally again. Then, the first inner flow path, the third inner flow path, and the fourth inner flow path are machined again using a numerical control machining method to ensure the flow path size requirements.

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