CN112962092A - Method for repairing abrasion of spline pipe sleeve teeth of aircraft engine - Google Patents
Method for repairing abrasion of spline pipe sleeve teeth of aircraft engine Download PDFInfo
- Publication number
- CN112962092A CN112962092A CN202110164839.9A CN202110164839A CN112962092A CN 112962092 A CN112962092 A CN 112962092A CN 202110164839 A CN202110164839 A CN 202110164839A CN 112962092 A CN112962092 A CN 112962092A
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- CN
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- Prior art keywords
- spraying
- repairing
- aircraft engine
- sleeve
- sleeve gear
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 35
- 238000005299 abrasion Methods 0.000 title claims abstract description 12
- 238000005507 spraying Methods 0.000 claims abstract description 63
- 239000007921 spray Substances 0.000 claims abstract description 40
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 claims abstract description 24
- 239000000843 powder Substances 0.000 claims abstract description 16
- 229910052757 nitrogen Inorganic materials 0.000 claims abstract description 13
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 11
- 239000000956 alloy Substances 0.000 claims abstract description 11
- 238000000227 grinding Methods 0.000 claims abstract description 11
- 239000002994 raw material Substances 0.000 claims abstract description 7
- 239000002932 luster Substances 0.000 claims abstract description 6
- 239000011248 coating agent Substances 0.000 claims description 14
- 238000000576 coating method Methods 0.000 claims description 14
- 230000008439 repair process Effects 0.000 abstract description 14
- 230000000694 effects Effects 0.000 abstract description 7
- 238000010288 cold spraying Methods 0.000 description 7
- 229910052751 metal Inorganic materials 0.000 description 4
- 239000002184 metal Substances 0.000 description 4
- 238000007747 plating Methods 0.000 description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 2
- BQCADISMDOOEFD-UHFFFAOYSA-N Silver Chemical compound [Ag] BQCADISMDOOEFD-UHFFFAOYSA-N 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- QJGQUHMNIGDVPM-UHFFFAOYSA-N nitrogen group Chemical group [N] QJGQUHMNIGDVPM-UHFFFAOYSA-N 0.000 description 2
- 239000004332 silver Substances 0.000 description 2
- 239000000758 substrate Substances 0.000 description 2
- 229910001316 Ag alloy Inorganic materials 0.000 description 1
- 229910000881 Cu alloy Inorganic materials 0.000 description 1
- 229910000746 Structural steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 229910000816 inconels 718 Inorganic materials 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000003208 petroleum Substances 0.000 description 1
- 229910052709 silver Inorganic materials 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Images
Classifications
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C24/00—Coating starting from inorganic powder
- C23C24/02—Coating starting from inorganic powder by application of pressure only
- C23C24/04—Impact or kinetic deposition of particles
- C23C24/045—Impact or kinetic deposition of particles by trembling using impacting inert media
Abstract
The invention relates to the field of repair methods in the field of aircraft engines, in particular to a repair method for abrasion of an aircraft engine spline pipe sleeve gear, which has better repair effect and excellent performance after repair, and comprises the following steps: a. firstly, grinding the worn part of the sleeve tooth to be repaired, exposing metallic luster, taking IN718 high-temperature alloy powder as a repairing raw material, taking nitrogen as an air source, and performing spray repairing on the surface of the sleeve tooth by adopting a cold spray method, wherein the spray repairing is performed IN three stages; b. and after the spraying is finished, grinding the sleeve gear until the repair requirement is met. The method is particularly suitable for the repair process of abrasion of the spline pipe sleeve teeth of the aircraft engine.
Description
Technical Field
The invention relates to the field of repair methods in the field of aircraft engines, in particular to a repair method for abrasion of spline pipe sleeve teeth of an aircraft engine.
Background
The existing aircraft engine spline pipe rotates together with a tensioning nut and a tensioning pipe in the working process of an engine, and before the engine stops and stops rotating, a low turbine and the tensioning pipe move in the radial direction and the axial direction and generate collision and abrasion with the spline pipe sleeve teeth. The spline pipe is made of TC6 titanium alloy, the tensioning pipe is made of structural steel 1Cr16Co5Ni2Mo2WVNbN, the hardness of the spline pipe is smaller than that of the tensioning pipe, therefore, wear of the spline pipe sleeve teeth is often caused, after the spline pipe sleeve teeth are worn, copper plating and silver plating repair are carried out on the spline pipe sleeve teeth in the traditional repair method, and the thickness of a plating layer is (0.1 +/-0.01) mm. However, the coating has low hardness and rough surface, so the coating is quickly worn in work and has poor anti-collision and anti-abrasion effects. Because the tooth profile of the spline pipe sleeve is complex, no effective repairing method exists at present.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for repairing abrasion of a spline pipe sleeve gear of an aircraft engine, which has better repairing effect and excellent performance after repairing.
The technical scheme adopted by the invention for solving the technical problems is as follows: the method for repairing the abrasion of the spline pipe sleeve teeth of the aircraft engine comprises the following steps: a. firstly, grinding the worn part of the sleeve tooth to be repaired, exposing metallic luster, taking IN718 high-temperature alloy powder as a repairing raw material, taking nitrogen as an air source, and performing spray repairing on the surface of the sleeve tooth by adopting a cold spray method, wherein the spray repairing is performed IN a three-stage mode: for the first spraying, the sleeve gear rotates around the central axis along the clockwise rotation direction, and the spraying direction of the spray gun is the reverse sleeve gear rotation direction and the sleeve gear is subjected to full-coating spraying; spraying for the second time, wherein the sleeve gear rotates around the central axis along the anticlockwise rotation direction, and the spraying direction of the spray gun is the reverse rotation direction of the sleeve gear and the sleeve gear is subjected to full-coating spraying; spraying for the third time, wherein the sleeve gear rotates around the central axis along the anticlockwise rotation direction, and the spraying direction of the spray gun faces the central axis direction of the sleeve gear and full-coating spraying is carried out; b. and after the spraying is finished, grinding the sleeve gear until the repair requirement is met.
Further, in the step a, the inlet temperature of nitrogen of a spray gun used for spraying is 450-500 ℃, and the pressure is 0.8-1.0 MPa.
Furthermore, in the step a, the powder feeding amount is 5-6 g/min.
Further, in the step a, the distance between the outlet of the spray gun and the surface of the base body of the sleeve tooth is 10-15 mm.
Further, in the step a, the moving speed of the spray gun is 2-3 mm/s.
Further, in the step a, the spraying thickness of the first spraying is 0.2 mm.
Further, in the step a, the spraying thickness of the second spraying is 0.2 mm.
Further, in the step a, the third spraying is performed to a thickness of 0.2 mm.
The invention has the beneficial effects that: the method comprises the steps of firstly, adopting IN718 high-temperature alloy powder as a repairing raw material, and simultaneously, adopting nitrogen as an air source to carry out spray repair on the surface of the sleeve gear by adopting a cold spray method. The fretting wear resistance of the IN718 high-temperature alloy coating repaired by cold spraying is higher than that of copper, silver and titanium alloy, and long-term use can be ensured. The IN718 superalloy powder is added to the ultrasonic gas stream by cold spray and accelerated impact onto the metal surface to form a high density coating with good adhesion. Meanwhile, the sectional spraying is adopted, so that the whole tooth surface can be completely coated, and the spraying effect is ensured. The method is particularly suitable for the repair process of abrasion of the spline pipe sleeve teeth of the aircraft engine.
Drawings
FIG. 1 is a schematic view of the first spraying of the present invention.
FIG. 2 is a schematic view of a second spray application of the present invention.
Fig. 3 is a schematic view of a third spray application of the present invention.
Labeled as: a set of teeth 1, a rotation direction 2 and a spraying direction 3.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
The method for repairing the abrasion of the spline sleeve teeth of the aircraft engine shown in figures 1, 2 and 3 comprises the following steps: a. firstly, grinding the worn part of the sleeve tooth to be repaired, exposing metallic luster, taking IN718 high-temperature alloy powder as a repairing raw material, taking nitrogen as an air source, and performing spray repairing on the surface of the sleeve tooth 1 by adopting a cold spray method, wherein the spray repairing is performed IN a three-stage mode: for the first spraying, the sleeve gear 1 rotates around the central axis along the clockwise rotation direction 2, at the moment, the spraying direction 3 of the spray gun is the rotation direction 2 of the reverse sleeve gear 1, and the sleeve gear 1 is subjected to full-coating spraying; spraying for the second time, wherein the sleeve gear 1 rotates around the central axis along the anticlockwise rotation direction 2, the spraying direction 3 of the spray gun is the reverse rotation direction 2 of the sleeve gear 1, and the sleeve gear 1 is subjected to full-coating spraying; spraying for the third time, wherein the sleeve gear 1 rotates around the central axis along the anticlockwise rotation direction 2, and the spraying direction 3 of the spray gun faces the central axis direction of the sleeve gear 1 and full-coating spraying is carried out; b. and after the spraying is finished, grinding the sleeve gear 1 until the repairing requirement is met.
The IN718 high-temperature alloy powder is totally called Inconel 718 high-temperature alloy powder, is mainly used for manufacturing and repairing various parts with complex shapes, and is widely used IN aerospace, nuclear energy, petroleum industry and extrusion dies. As the invention adopts three-stage spraying, as shown IN figures 1, 2 and 3, when the first spraying and the second spraying are carried out, the spraying direction 3 of the spray gun and the rotating direction 2 of the sleeve gear 1 are opposite, namely the spraying direction 3 is opposite to the rotating direction 2, thereby ensuring that the IN718 high-temperature alloy powder is accelerated and impacted on the metal surface IN the ultrasonic gas flow to form a high-density coating with good bonding force.
In order to further improve the spraying effect, the following technical scheme is preferred: in the step a, the inlet temperature of nitrogen of a spray gun used for spraying is 450-500 ℃, and the pressure is 0.8-1.0 MPa, so that the sprayed nitrogen is ensured to be in a better working state. In the preferable step a, the powder feeding amount is 5-6 g/min, so that the sprayed layer thickness and the spraying effect are in a better state. Based on the same principle, in the preferable step a, the distance between the outlet of the spray gun and the surface of the base body of the sleeve tooth 1 is 10-15 mm. And in the preferable step a, the moving speed of the spray gun is 2-3 mm/s.
In the actual spraying, the spraying thickness of the first spraying in the step a is preferably 0.2mm, the spraying thickness of the second spraying in the step a is preferably 0.2mm, and the spraying thickness of the third spraying in the step a is preferably 0.2 mm. Therefore, the subsequent grinding processing is convenient under the condition of ensuring the thickness of the sprayed layer.
Examples
Example 1
The method comprises the following steps that (1) sleeve teeth of a spline are worn in the using process of a certain aeroengine, and the worn part of the sleeve teeth is manually polished to expose metal luster; the IN718 high-temperature alloy powder is used as a repairing raw material, and a cold spraying method is adopted for repairing. The cold spraying parameters are that the air source is nitrogen, the inlet temperature of the nitrogen is 450 ℃, the pressure is 1.0MPa, the powder feeding amount is 5.5g/min, the distance between the spray gun and the surface of the substrate is 12mm, and the moving speed of the spray gun is 2 mm/s. And after cold spraying, grinding the key teeth to reach the size of the drawing.
The repaired spline tube can be normally used after being assembled, and the use requirement is met.
Example 2
The method comprises the following steps that (1) sleeve teeth of a spline are worn in the using process of a certain aeroengine, and the worn part of the sleeve teeth is manually polished to expose metal luster; the IN718 high-temperature alloy powder is used as a repairing raw material, and a cold spraying method is adopted for repairing. The cold spraying parameters are that the air source is nitrogen, the inlet temperature of the nitrogen is 500 ℃, the pressure is 0.8MPa, the powder feeding amount is 5.5g/min, the distance between the spray gun and the surface of the substrate is 15mm, and the moving speed of the spray gun is 3 mm/s. And (5) grinding the sleeve gear after cold spraying to reach the size of the drawing.
The repaired spline tube can be normally used after being assembled, and the use requirement is met.
The spline pipe sleeve tooth repaired by the method has the advantages of excellent repairing effect, excellent performance after repair, very obvious technical advantages and very wide market popularization prospect.
Claims (8)
1. The method for repairing abrasion of spline pipe sleeve teeth of the aircraft engine is characterized by comprising the following steps of:
a. firstly, grinding the worn part of the set tooth (1) to be repaired, exposing metallic luster, taking IN718 high-temperature alloy powder as a repairing raw material, taking nitrogen as an air source, and performing spray repairing on the surface of the set tooth (1) by adopting a cold spray method, wherein the spray repairing is performed IN a three-stage mode: the first spraying, the sleeve gear (1) rotates around the central axis along the clockwise rotation direction (2), at the moment, the spraying direction (3) of the spray gun is the rotation direction (2) of the reverse sleeve gear (1), and the sleeve gear (1) is subjected to full-coating spraying; spraying for the second time, wherein the sleeve gear (1) rotates around the central axis along the anticlockwise rotating direction (2), the spraying direction (3) of the spray gun is the rotating direction (2) of the reverse sleeve gear (1), and the sleeve gear (1) is subjected to full-coating spraying; spraying for the third time, wherein the sleeve gear (1) rotates around the central axis along the anticlockwise rotating direction (2), and the spraying direction (3) of the spray gun faces the central axis of the sleeve gear (1) and full-coating spraying is carried out;
b. and after the spraying is finished, grinding the sleeve gear (1) until the repairing requirement is met.
2. The method for repairing wear of spline tube sleeve teeth of an aircraft engine according to claim 1, wherein: in the step a, the inlet temperature of nitrogen of a spray gun used for spraying is 450-500 ℃, and the pressure is 0.8-1.0 MPa.
3. The method for repairing wear of spline tube sleeve teeth of an aircraft engine according to claim 1, wherein: in the step a, the powder feeding amount is 5-6 g/min.
4. The method for repairing wear of spline tube sleeve teeth of an aircraft engine according to claim 1, wherein: in the step a, the distance between the outlet of the spray gun and the surface of the base body of the sleeve gear (1) is 10-15 mm.
5. The method for repairing wear of spline tube sleeve teeth of an aircraft engine according to claim 1, wherein: in the step a, the moving speed of the spray gun is 2-3 mm/s.
6. A method for repairing wear of spline tube sleeve teeth of an aircraft engine according to claim 1, 2, 3, 4 or 5, characterized in that: in the step a, the spraying thickness of the first spraying is 0.2 mm.
7. A method for repairing wear of spline tube sleeve teeth of an aircraft engine according to claim 1, 2, 3, 4 or 5, characterized in that: in the step a, the spraying thickness of the second spraying is 0.2 mm.
8. A method for repairing wear of spline tube sleeve teeth of an aircraft engine according to claim 1, 2, 3, 4 or 5, characterized in that: in the step a, the spraying thickness of the third spraying is 0.2 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110164839.9A CN112962092A (en) | 2021-02-05 | 2021-02-05 | Method for repairing abrasion of spline pipe sleeve teeth of aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110164839.9A CN112962092A (en) | 2021-02-05 | 2021-02-05 | Method for repairing abrasion of spline pipe sleeve teeth of aircraft engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112962092A true CN112962092A (en) | 2021-06-15 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110164839.9A Pending CN112962092A (en) | 2021-02-05 | 2021-02-05 | Method for repairing abrasion of spline pipe sleeve teeth of aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112962092A (en) |
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| CN110145239A (en) * | 2019-05-20 | 2019-08-20 | 中国地质大学（北京） | It drills inserted, rock bit and drills inserted processing method |
| US20200180211A1 (en) * | 2018-12-10 | 2020-06-11 | Src Corporation | Gear product having reinforced deposition surface and deposition system for manufacturing the same |
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-
2021
- 2021-02-05 CN CN202110164839.9A patent/CN112962092A/en active Pending
Patent Citations (17)
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| CN1766152A (en) * | 2005-11-17 | 2006-05-03 | 广州有色金属研究院 | Corrugated roller hot spraying production and restoring method |
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Application publication date: 20210615 |