# US 2019/0168327 A1 · Method for producing turbine blade

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- Number: US 2019/0168327 A1
- Document ID: US20190168327A1
- Status: Published application
- Kind: A1
- Application number: 16/321,276
- Filed: 2017-10-05
- Published: 2019-06-06
- Earliest claimed: 2016-10-07
- Assignees: Mitsubishi Hitachi Power Systems, Ltd.
- Applicants: Mitsubishi Hitachi Power Systems, Ltd.
- Inventors: Daisuke YOSHIDA; Kazuto NISHIZAWA; Masaki TANEIKE; Ichiro NAGANO; Naotoshi OKAYA; Yoshiyuki INOUE; Hisataka KAWAI; Hisashi KITAGAKI
- Web page: https://patentgrep.com/patent/US20190168327A1

## CPC

- B23K 1/0018: {Brazing of turbine parts}
- B23K 1/00: Soldering, e.g. brazing, or unsoldering (B23K3/00 takes precedence)
- C22C 19/056: {with the maximum Cr content being at least 10% but less than 20%}
- C22F 1/10: of nickel or cobalt or alloys based thereon
- C23C 4/02: Pretreatment of the material to be coated, e.g. for coating on selected surface areas
- C23C 4/06: Metallic material
- C23C 4/073: containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
- C23C 4/08: containing only metal elements (C23C4/073 takes precedence)
- C23C 4/129: Flame spraying
- C23C 4/134: Plasma spraying
- C23C 4/18: After-treatment
- F01D 5/28: Selecting particular materials; {Particular measures relating thereto;} Measures against erosion or corrosion
- F01D 5/286: {Particular treatment of blades, e.g. to increase durability or resistance against corrosion or erosion (F01D5/288 takes precedence)}
- F01D 5/288: {Protective coatings for blades}
- F01D 9/02: Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)}
- F01D 25/00: Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- B23K 2101/001: {Turbines}
- B23K 2103/08: Non-ferrous metals or alloys
- C22C 19/05: with chromium
- F05D 2230/237: Brazing
- F05D 2230/41: Hardening; Annealing
- F05D 2230/42: by hot isostatic pressing
- F05D 2230/90: Coating; Surface treatment
- F05D 2300/17: Alloys
- F05D 2300/611: Coating
- B23K: SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- C22C: ALLOYS (treatment of alloys C21D, C22F)
- C22F: CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS (surface treatment of metallic material involving at least one process provided for in class C23 and at least one process covered by this subclass, C23F17/00)
- 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 (making metal-coated products by extrusion B21C23/22; covering with metal by connecting pre-existing layers to articles, see the relevant places, e.g. B21D39/00, B23K; metallising of glass C03C; metallising mortars, concrete, artificial stone, ceramics or natural stone C04B41/00; enamelling of, or applying a vitreous layer to, metals C23D; treating metal surfaces or coating of metals by electrolysis or electrophoresis C25D; single-crystal film growth C30B; by metallising textiles D06M11/83; decorating textiles by locally metallising D06Q1/04)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS

## Abstract

A method for producing a turbine blade includes performing brazing treatment, performing annealing, and subjecting a base material to solutionizing treatment. In the brazing treatment, a brazing material is welded to be joined to the base material of a turbine blade by operating a heater to perform heating at a first temperature under a state in which the base material having the brazing material arranged thereon is placed in a predetermined heating furnace including the heater. In annealing, the base material is cooled by stopping the heater and lowering a furnace internal temperature after the brazing treatment. In the solutionizing treatment, ductility of the base material is improved through heating at a second temperature lower than the first temperature after the annealing.

## Claims

### Claim 1

A method for producing a turbine blade, comprising:
performing brazing treatment for welding a brazing material to be joined to a base material of a turbine blade by operating a heater to perform heating at a first temperature under a state in which the base material having the brazing material arranged thereon is placed in a predetermined heating furnace including the heater;
performing annealing for cooling the base material by stopping the heater and lowering a furnace internal temperature after the brazing treatment; and
subjecting the base material to solutionizing treatment by heating the base material at a second temperature lower than the first temperature after the annealing.

### Claim 2 (depends on 1)

The method for producing a turbine blade according to claim 1, further comprising:
forming first coating through use of a metallic material having a higher wear-resisting property than a wear-resisting property of the base material, the first coating formed on a portion of the base material corresponding to a contact surface of the turbine blade; and
forming second coating through use of a metallic material having a higher oxidation-resisting property than an oxidation-resisting property of the base material, the second coating formed on a surface of the base material,
wherein the brazing treatment is performed after the first coating and the second coating are formed.

### Claim 3 (depends on 1)

The method for producing a turbine blade according to claim 1, further comprising performing quenching for cooling the base material by supplying a cooling air into the heating furnace after the furnace internal temperature reaches to a predetermined temperature through the annealing,
wherein the solutionizing treatment is performed after the quenching.

### Claim 4 (depends on 1)

The method for producing a turbine blade according to claim 1, further comprising:
forming first coating through use of a metallic material having a higher wear-resisting property than a wear-resisting property of the base material, the first coating formed on a portion of the base material corresponding to a contact surface of the turbine blade;
forming second coating through use of a metallic material having a higher oxidation-resisting property than an oxidation-resisting property of the base material, the second coating formed on a surface of the base material; and
performing quenching for cooling the base material by supplying a cooling air into the heating furnace after the furnace internal temperature reaches a predetermined temperature through the annealing,
wherein the first coating and the second coating are formed after the brazing treatment, the annealing, and the quenching are performed, and
wherein the solutionizing treatment is performed after the first coating and the second coating are formed.

### Claim 5 (depends on 2)

The method for producing a turbine blade according to claim 2, further comprising:
forming an undercoat on a surface of the base material as the second coating; and
forming a topcoat on a surface of the undercoat after the undercoat is formed,
wherein the topcoat is formed after the brazing treatment and the solutionizing treatment are performed.

### Claim 6 (depends on 2)

The method for producing a turbine blade according to claim 2, wherein the undercoat is formed after the brazing treatment and the solutionizing treatment are performed.

### Claim 7 (depends on 2)

The method for producing a turbine blade according to claim 2, further comprising performing aging treatment by heating the base material after the solutionizing treatment,
wherein the topcoat is formed after the aging treatment.

### Claim 8 (depends on 1)

The method for producing a turbine blade according to claim 1, further comprising performing adjusting treatment for causing the furnace internal temperature to rise to the second temperature by operating the heater after the furnace internal temperature reaches a third temperature lower than the second temperature through the annealing.

### Claim 9 (depends on 1)

The method for producing a turbine blade according to claim 1, wherein, in the annealing, a temperature of the base material is lowered at a temperature lowering rate of from 3° C./min to 20° C./min.