Method of laser induction composite cladding gradient function thermal barrier coating

Abstract

The invention discloses a method of a laser induction composite cladding gradient function thermal barrier coating, which is characterized in that the methods and steps are as follows: (1) the surface of base material is provided with processing of rust removing, oil removing, cleaning and sand spraying; (2) meanwhile, the inert protective gas is blown into an induction heating zone through utilizing a copper pipe, which prevents the high-temperature oxidation; (3) a focused laser beam and a powder nozzle of an automatic double-hopper powder feeder are located in the induction heating zone, and the composition of the laser heat source and the induction heating source can be realized; (4) a numerical control machine is moved 70-30% of the laser spot diameter along the vertical direction of the laser scanning speed; (5) the mass percentage content of a ceramic phase in the composite powder is led to be increased by 0-90 wt.%; (6) steps (2)-(5) are repeated until the required thickness of the coating is achieved; otherwise, the work is ended. The advantages of the invention are as follows: (1) the size, the shape and the part needing to process of the base material are not limited; (2) for the gradient function thermal barrier coating, the content of the ceramic phase in the coating presents change of gradient and is controllable along the thickness direction of the coating; (3) the whole gradient function thermal barrier coating has no air hole and crack; (4) the service life is greatly increased.

Description

technical field

[0001] The invention relates to a method for laser induction composite cladding gradient functional thermal barrier coating. Background technique

[0002] With the development of aviation gas turbines in the direction of high flow ratio, high thrust-to-weight ratio, and high inlet temperature, the inlet temperature of the turbine continues to increase, and it is currently close to 2000K. In order to improve the service life of high-temperature hot-end components such as turbine outer rings and blades, and ensure the safe and stable operation of gas turbines, in addition to improving the composition, preparation process and blade design of superalloys, the use of protective thermal barrier coatings is currently the most effective method .

[0003] At present, the technologies for preparing thermal barrier coatings on the surface of superalloy hot end components mainly include plasma spraying, electron beam-physical vapor deposition (EB-PVD), laser cladding, e...

Examples

Embodiment 1

[0021] Preparation of NiCrAlY / (ZrO on the surface of nickel base superalloy 2 +(6~8%)CeO 2 ) Gradient functional thermal barrier coating, the thickness of the coating is 6mm, in which ceramic phase cerium oxide stabilized zirconia (ZrO 2 +(6~8%)CeO 2 ) embedded in the bonding metal NiCrAlY, and along the thickness direction of the coating, it presents arbitrarily adjustable gradient distribution in the range of 0-90wt.%.

[0022] The implementation process of this embodiment is, as figure 1 and figure 2 shown.

[0023] (1) Selection and preparation of cladding materials: the bonding metal is NiCrAlY alloy powder, and its chemical composition is (mass percentage) 50-70% Ni, 19-25% Cr, 6-8% Al, 0.08-1.5% Y , the particle size is 45-90 μm, and the ceramic phase is ceria-stabilized zirconia (ZrO 2 +(6~8%)CeO 2 ), with a particle size of 20-40 μm, NiCrAlY alloy powder and ceria-stabilized zirconia (ZrO 2 +(6~8%)CeO 2 ) particles into the two loading hoppers 7, 7' of the d...

Embodiment 2

[0031] Preparation of NiCoCrAlY / Ti on the Surface of Ni-base Superalloy 3 Al gradient functional thermal barrier coating, the thickness of the coating is 3mm, in which the ceramic phase Ti 3 Al is embedded in the bonding metal NiCoCrAlY, and presents arbitrarily adjustable gradient distribution in the range of 0-90wt.% along the thickness direction of the coating.

[0032] The implementation process of this embodiment is, as figure 1 and figure 2 shown.

[0033] (1) Selection and preparation of cladding materials: the bonding metal is NiCoCrAlY alloy powder, and its chemical composition is (weight percent) 40-60% Ni, 18-22% Co, 19-25% Cr, 6-8% Al , 0.08-1.5% Y, the particle size is 45-90 μm; the ceramic phase is an intermetallic compound Ti 3 Al particles, the particle size of which is 40-60 μm, and then NiCoCrAlY alloy powder and Ti 3 The Al particles are loaded into the two loading hoppers 7 and 7' of the double-bucket automatic powder feeder 9 respectively; the surfac...

technical field

[0001] The invention relates to a method for laser induction composite cladding gradient functional thermal barrier coating. Background technique

[0002] With the development of aviation gas turbines in the direction of high flow ratio, high thrust-to-weight ratio, and high inlet temperature, the inlet temperature of the turbine continues to increase, and it is currently close to 2000K. In order to improve the service life of high-temperature hot-end components such as turbine outer rings and blades, and ensure the safe and stable operation of gas turbines, in addition to improving the composition, preparation process and blade design of superalloys, the use of protective thermal barrier coatings is currently the most effective method .

[0003] At present, the technologies for preparing thermal barrier coatings on the surface of superalloy hot end components mainly include plasma spraying, electron beam-physical vapor deposition (EB-PVD), laser cladding, e...

Examples

Embodiment 1

[0021] Preparation of NiCrAlY / (ZrO on the surface of nickel base superalloy 2 +(6~8%)CeO 2 ) Gradient functional thermal barrier coating, the thickness of the coating is 6mm, in which ceramic phase cerium oxide stabilized zirconia (ZrO 2 +(6~8%)CeO 2 ) embedded in the bonding metal NiCrAlY, and along the thickness direction of the coating, it presents arbitrarily adjustable gradient distribution in the range of 0-90wt.%.

[0022] The implementation process of this embodiment is, as figure 1 and figure 2 shown.

[0023] (1) Selection and preparation of cladding materials: the bonding metal is NiCrAlY alloy powder, and its chemical composition is (mass percentage) 50-70% Ni, 19-25% Cr, 6-8% Al, 0.08-1.5% Y , the particle size is 45-90 μm, and the ceramic phase is ceria-stabilized zirconia (ZrO 2 +(6~8%)CeO 2 ), with a particle size of 20-40 μm, NiCrAlY alloy powder and ceria-stabilized zirconia (ZrO 2 +(6~8%)CeO 2 ) particles into the two loading hoppers 7, 7' of the d...

Embodiment 2

[0031] Preparation of NiCoCrAlY / Ti on the Surface of Ni-base Superalloy 3 Al gradient functional thermal barrier coating, the thickness of the coating is 3mm, in which the ceramic phase Ti 3 Al is embedded in the bonding metal NiCoCrAlY, and presents arbitrarily adjustable gradient distribution in the range of 0-90wt.% along the thickness direction of the coating.

[0032] The implementation process of this embodiment is, as figure 1 and figure 2 shown.

[0033] (1) Selection and preparation of cladding materials: the bonding metal is NiCoCrAlY alloy powder, and its chemical composition is (weight percent) 40-60% Ni, 18-22% Co, 19-25% Cr, 6-8% Al , 0.08-1.5% Y, the particle size is 45-90 μm; the ceramic phase is an intermetallic compound Ti 3 Al particles, the particle size of which is 40-60 μm, and then NiCoCrAlY alloy powder and Ti 3 The Al particles are loaded into the two loading hoppers 7 and 7' of the double-bucket automatic powder feeder 9 respectively; the surfac...

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