Manufacturing method for turbine blade, and turbine blade

Patent metadata

Field	Value
Publication number	US-11371353-B2
Application number	US-201816647060-A
Country	US
Kind code	B2
Filing date	Jun 22, 2018
Priority date	Sep 19, 2017
Publication date	Jun 28, 2022
Grant date	Jun 28, 2022

Abstract

A method of manufacturing a turbine blade includes forming a blade body divided body constituting a blade body of the turbine blade by a three-dimensional lamination method; individually forming a plurality of shroud divided bodies constituting a shroud of the turbine blade for each of the shroud divided bodies by a three-dimensional lamination method; joining the shroud divided bodies together; and joining the blade body divided body and the shroud divided bodies.

First claim

The invention claimed is:

1. A method of manufacturing a stationary turbine blade, the method comprising:
three-dimensionally laminating blade body constituent material so as to form a blade divided body constituting a blade body of the stationary turbine blade;
three-dimensionally laminating each of a plurality of shroud divided bodies constituting a shroud of the stationary turbine blade;
joining the plurality of shroud divided bodies together by welding; and
joining the blade body and the plurality of shroud divided bodies,
wherein:
a lamination direction of the blade body is different from a lamination direction of the shroud;
at least one of the plurality of shroud divided bodies has, in an interior thereof, a cooling flow path with a cross-sectional shape having a long-side direction and a short-side direction; and
a lamination direction of the at least one of the plurality of shroud divided bodies is a direction along the long-side direction of the cross-sectional shape of the cooling flow path, and the cross-sectional shape is perpendicular to a flow direction of cooling air in the cooling flow path.

2. The method according to claim 1 ,
wherein an extension direction of the blade body and an extension direction of the shroud are set in the stationary turbine blade,
wherein the extension direction of the shroud is at a direction having an angle with respect to the extension direction of the blade body,
wherein three-dimensionally laminating the blade body constituent material so as to form the blade divided body includes performing lamination along the extension direction of the blade body, and
wherein three-dimensionally laminating each of the plurality of shroud divided bodies includes performing lamination along the extension direction of the shroud.

3. The method according to claim 1 , wherein three-dimensionally laminating each of the plurality of shroud divided bodies includes performing lamination in the long-side direction of the cross-sectional shape of the cooling flow path.

4. The method according to claim 1 , wherein three-dimensionally laminating each of the plurality of shroud divided bodies includes forming the plurality of shroud divided bodies such that a joined portion between the plurality of shroud divided bodies is provided at a position where a distance between the blade body and an end surface in an extension direction of the shroud is reduced.

5. The method according to claim 1 ,
wherein a fillet portion is provided in the blade body, and
wherein joining the blade body and the plurality of shroud divided bodies includes joining the blade body and the plurality of shroud divided bodies at a position avoiding the fillet portion.

6. The method according to claim 1 ,
wherein joining the plurality of shroud divided bodies together by welding includes laser powder overlay welding, and
wherein joining the blade body and the plurality of shroud divided bodies includes welding the blade body and the plurality of shroud divided bodies to each other by laser powder overlay welding.

7. The method according to claim 6 , wherein the laser powder overlay welding is performed using powder of the same material as the blade body constituent material and of the same material as a shroud constituent material constituting the shroud.

8. The method according to claim 6 ,
wherein the shroud has a gas path surface facing a blade body side, and
wherein joining the blade body and the plurality of shroud divided bodies includes providing a joining groove on a gas path surface side.

9. The method according to claim 1 ,
wherein three-dimensionally laminating the blade body constituent material so as to form the blade divided body includes three-dimensionally laminating a positioning portion at the blade divided body, and
wherein joining the blade body and the plurality of shroud divided bodies includes:
fixing the positioning portion of the blade divided body to a first jig and fixing the plurality of shroud divided bodies to a second jig;
aligning the blade divided body fixed to the first jig with the plurality of shroud divided bodies fixed to the second jig; and
joining the blade body and the plurality of shroud divided bodies while aligned.

10. A stationary turbine blade comprising:
a blade body in which blade body constituent material is laminated three-dimensionally; and
a shroud laminated three-dimensionally, formed separately from the blade body and joined to the blade body,
wherein:
a lamination direction of the blade body is different from a lamination direction of the shroud;
the shroud includes a plurality of shroud divided bodies joined together by welding;
at least one of the plurality of shroud divided bodies has, in an interior thereof, a cooling flow path with a cross-sectional shape having a long-side direction and a short-side direction; and
a lamination direction of the at least one of the plurality of shroud divided bodies is a direction along the long-side direction of the cross-sectional shape of the cooling flow path, and the cross-sectional shape is perpendicular to a flow direction of cooling air in the cooling flow path.

11. The stationary turbine blade according to claim 10 , wherein:
an extension direction of the blade body and an extension direction of the shroud are set in the stationary turbine blade;
the extension direction of the shroud is at a direction having an angle with respect to the extension direction of the blade body;
the lamination direction of the blade body is a direction along the extension direction of the blade body; and
the lamination direction of the shroud is a direction along the extension direction of the shroud.

12. The stationary turbine blade according to claim 10 , wherein:
the blade body includes a fillet portion;
the blade body and the shroud are joined to each other by a joined portion; and
the joined portion is formed at a position outside the fillet portion.

13. The stationary turbine blade according to claim 12 , wherein:
the shroud has a gas path surface facing a blade body side; and
the joined portion is flush with the gas path surface.

Assignees

• Mitsubishi Hitachi Power Sys Ltd
• Mitsubishi Heavy Ind Ltd

Inventors

• Atsumi Hidekatsu
• Motoyama Norihiko
• Tanigawa Shuji

Classifications

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• B22F10/40

  Structures for supporting workpieces or articles during manufacture and removed afterwards · CPC title

• B22F10/20

  Direct sintering or melting · CPC title

• F01D5/14 Primary

  Form or construction (selecting particular materials, measures against erosion or corrosion F01D5/28) · CPC title

• B22F5/04

  of turbine blades · CPC title