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CN-121988975-A - Composite repair method for ablation of guide vane of aero-engine

CN121988975ACN 121988975 ACN121988975 ACN 121988975ACN-121988975-A

Abstract

The invention relates to the technical field of aero-engine repair, in particular to a composite repair method for ablation of a guide vane of an aero-engine. The method comprises the steps of polishing an ablation area of an aeroengine guide blade, coating the polished ablation area with cobalt-based brazing filler metal, performing vacuum brazing at a vacuum degree of below 4X 10 ‑2 Pa to obtain the aeroengine guide blade with a brazing repair area, and performing arc ion plating on the brazing repair area of the aeroengine guide blade with the brazing repair area to increase a surface coating to obtain the aeroengine guide blade with the completely repaired ablation area. The invention completely repairs the ablated region, and the completely repaired region can still work at high temperature of 1100 ℃.

Inventors

  • XU SHIMING
  • DONG BAOJUN
  • ZHAO WEN
  • ZHOU JUN
  • LI WEI
  • Lin Kaizhang
  • REN YANG
  • SHI XIANKE
  • WEI SHUANG

Assignees

  • 成都国营锦江机器厂

Dates

Publication Date
20260508
Application Date
20260224

Claims (10)

  1. 1. The composite repairing method for the ablation of the aero-engine guide vane is characterized by comprising the following steps of polishing an ablation area of the aero-engine guide vane, coating the polished ablation area with cobalt-based brazing filler metal, and performing vacuum brazing at a vacuum degree of below 4X 10 -2 Pa to obtain the aero-engine guide vane with a brazing repair area; And performing arc ion plating on the brazing repair area of the aero-engine guide vane in the brazing repair area to increase the surface coating, thereby obtaining the aero-engine guide vane in the completely repaired ablation area.
  2. 2. The composite repair method for the ablation of the aero-engine guide vane is characterized by comprising the specific steps of polishing an ablation area of the aero-engine guide vane by adopting a pneumatic polisher until the metallic luster is exposed, and polishing the ablation area with the diameter of not less than 10 mm.
  3. 3. A composite repair method for aircraft engine guide vane ablation according to claim 1, wherein the coating thickness of the cobalt-based braze is no less than the deepest pit of the ablated region of the aircraft engine guide vane.
  4. 4. A composite repair method for aircraft engine guide vane ablation according to claim 1, wherein the cobalt-based braze comprises braze powder and an adhesive.
  5. 5. A composite repair method for aircraft engine guide vane ablation according to claim 4, wherein said braze powder comprises Co43CrNiWBSi; The adhesive includes Nicrobraz media 520.
  6. 6. The composite repair method for ablation of guide vanes of an aeroengine according to claim 4, wherein the mass ratio of the brazing filler metal powder to the adhesive is 5-15:1.
  7. 7. The composite repair method for ablation of the guide vane of the aeroengine according to any one of claims 1 to 6 is characterized in that the vacuum brazing is carried out in a specific mode that the vacuum degree is kept below 4X 10 -2 Pa in a heating process of a vacuum brazing furnace, the vacuum degree is heated to 350-450 ℃ in 35-50 min, the temperature is kept for 10-25 min, the vacuum brazing is continuously heated to 900-1000 ℃ in 45-60 min, the vacuum brazing is continuously heated to 1150-1210 ℃ in 20-35 min, the vacuum brazing is continuously heated for 2-10 min, the vacuum brazing is cooled to 1020-1100 ℃ in 20-35 min, the vacuum brazing is carried out in 4-h min, and finally argon is cooled or forced cooled to 80 ℃ along with the furnace and discharged from the furnace.
  8. 8. A composite repair method for aircraft engine stator blade ablation according to any one of claims 1 to 6, wherein the target for arc ion plating is a NiCrAlY target.
  9. 9. The composite repair method for the ablation of the aeroengine guide blade according to claim 8 is characterized in that in a vacuum multi-arc ion plating machine, the vacuum degree is kept at 0.25-0.45 Pa, the etching time is 20-50 min, the voltage is kept at 20-70V, the current is kept at 80-150A, the vacuum degree is kept at 0.25-0.45 Pa, the deposition time is 300-400 min, the aeroengine guide blade with the surface coating added is transferred into a vacuum diffusion furnace, vacuumizing is firstly carried out until the vacuum degree is lower than 5.0X10 -3 Pa, the partial pressure of argon is increased to 20-80 Pa when the temperature is raised to above 300 ℃ until the end of heat preservation, the heating temperature is set to 600-700 ℃, the heat preservation time is 0.5-1 h, the temperature is raised to 900-1000 ℃ and the heat preservation time is 2.5-3.0 h.
  10. 10. The composite repair method for ablation of an aircraft engine guide vane of claim 8, wherein the thickness of the surface coating is 0.02-0.09 mm.

Description

Composite repair method for ablation of guide vane of aero-engine Technical Field The invention relates to the technical field of aero-engine repair, in particular to a composite repair method for ablation of a guide vane of an aero-engine. Background The existing axial-flow aeroengine has the functions of converting the energy of high-temperature gas flow into mechanical work and transmitting the mechanical work to a gas compressor and an accessory transmission device, wherein guide blades are used for providing high-temperature gas with reasonable angles for rear parts. The guide vane is flushed by high-temperature fuel gas in the service process, and a large amount of ablation pit phenomena are easily generated at the position of the exhaust edge of the vane, as shown in figure 1. The guide vane material is cast high-temperature alloy, has higher high-temperature strength, but has poorer heat and corrosion resistance. When the guide vane is ablated, high-temperature fuel gas passing through the ablation surface can be influenced, the rotating speed of a rotor of the fuel gas generator is influenced, the power of the engine is reduced, even the engine is not successfully started, and the flight safety is seriously influenced. At present, the blade repairing technology mainly comprises laser material adding, friction welding, electric arc material adding and other technologies, and the traditional technology can only repair a single blade in the blade repairing process and has low working efficiency. In view of this, the present invention provides a composite repair method for aircraft engine guide vane ablation. Disclosure of Invention The invention aims to solve the technical problem of providing a composite repair method for ablation of a guide vane of an aeroengine. The method aims to establish a complete repair method for ablation faults of the guide vane blades of the aeroengine. The technical scheme for solving the technical problems is as follows: Polishing an ablation area of an aeroengine guide blade, coating the polished ablation area with cobalt-based brazing filler metal, and performing vacuum brazing at a vacuum degree of below 4X 10 -2 Pa to obtain the aeroengine guide blade with a brazed repair area; And performing arc ion plating on the brazing repair area of the aero-engine guide vane in the brazing repair area to increase the surface coating, thereby obtaining the aero-engine guide vane in the completely repaired ablation area. On the basis of the technical scheme, the invention can be improved as follows. Further, the polishing method specifically comprises the steps of polishing an ablation area of the guide vane of the aeroengine by adopting a pneumatic polisher until the metallic luster is exposed, and polishing the ablation area with the diameter not less than 10 mm. Further, the coating thickness of the cobalt-based brazing filler metal is not lower than the deepest pit of the ablation area of the guide vane of the aeroengine, and the ablation area of the guide vane is completely covered. Further, the cobalt-based solder includes a solder powder and a binder. Further, the solder powder includes Co43CrNiWBSi; The adhesive includes Nicrobraz media 520. Further, the mass ratio of the brazing filler metal powder to the adhesive is 5-15:1. The vacuum brazing method comprises the specific steps of keeping the vacuum degree below 4X 10 -2 Pa in a vacuum brazing furnace heating process, heating to 350-450 ℃ in 35-50 min, preserving heat for 10-25 min, continuously heating to 900-1000 ℃ in 45-60 min, preserving heat for 10-25 min, continuously heating to 1150-1210 ℃ in 20-35 min, preserving heat for 2-10 min, cooling to 1020-1100 ℃ in 20-35 min, preserving heat for 4-h, and finally discharging from the furnace after furnace cooling or argon filling forced cooling to below 80 ℃. Further, the target material adopted by the arc ion plating is a NiCrAlY target material. The arc ion plating method comprises the steps of in a vacuum multi-arc ion plating machine, maintaining the current at 30-50A and the voltage at 100-200V, maintaining the vacuum degree at 0.25-0.45 Pa, etching for 20-50 min, maintaining the voltage at 20-70V and the current at 80-150A and the vacuum degree at 0.25-0.45 Pa, depositing for 300-400 min, transferring the aeroengine guide blade with the surface coating into a vacuum diffusion furnace, vacuumizing to a vacuum degree lower than 5.0X10 -3 Pa, filling argon to a partial pressure of 20-80 Pa when the temperature is raised to above 300 ℃ and the heat preservation is finished, setting the heating temperature to 600-700 ℃, preserving the heat for 0.5-1 h, and then raising the temperature to 900-1000 ℃ and preserving the heat for 2.5-3.0 h. Further, the thickness of the surface coating is 0.02-0.09 mm. The beneficial effects of the invention are as follows: (1) Compared with the prior art which only pays attention to metal matrix repair and only involves a welding method, th