Turbine nozzle components having reduced flow areas

Patent metadata

Field	Value
Publication number	US-9581035-B2
Application number	US-201514810802-A
Country	US
Kind code	B2
Filing date	Jul 28, 2015
Priority date	Feb 2, 2012
Publication date	Feb 28, 2017
Grant date	Feb 28, 2017

Abstract

Embodiments of a method for controllably reducing of the flow area of a turbine nozzle component are provided, as are embodiments of turbine nozzle components having reduced flow areas. In one embodiment, the method includes the steps of obtaining a turbine nozzle component having a plurality of turbine nozzle flow paths therethrough, positioning braze preforms in the plurality of turbine nozzle flow paths and against a surface of the turbine nozzle component, and bonding the braze preforms to the turbine nozzle component to achieve a controlled reduction in the flow area of the turbine nozzle flow paths.

First claim

What is claimed is:

1. A turbine nozzle component, comprising:
an inner endwall;
an outer endwall radially spaced from the inner endwall;
a plurality of nozzle vanes extending between the inner and outer endwalls, the plurality of nozzle vanes having leading and trailing edges;
a plurality of turbine nozzle flow paths extending through the turbine nozzle component and generally defined by the inner endwall, the outer endwall, and the plurality of nozzle vanes; and
braze preforms positioned in the turbine nozzle flow paths and bonded to at least one of the inner endwall and outer endwall reducing the flow area of the turbine nozzle flow paths, the braze preforms wrapping around the leading and trailing edges of the plurality of nozzle vanes;
wherein at least one of the braze preforms comprises a midline break dividing the braze preform into multiple pieces, which are bonded to one of the inner endwall and the outer endwall.

2. The turbine nozzle component of claim 1 wherein the braze preforms are further welded to at least one of the inner endwall and outer endwall.

3. The turbine nozzle component of claim 1 further comprising inner inter-blade flow areas provided on the inner endwall and bounding the plurality of flow paths, the plurality of braze preforms having planform geometries substantially conformal with the inner inter-blade flow areas.

4. The turbine nozzle component of claim 1 further comprising outer inter-blade flow areas provided on the outer endwall and bounding the plurality of flow paths, the plurality of braze preforms having planform geometries substantially conformal with the outer inter-blade flow areas.

5. The turbine nozzle component of claim 1 wherein the braze preforms are interspersed with the plurality of nozzle vanes.

6. The turbine nozzle component of claim 1 wherein the turbine nozzle component is produced from a parent superalloy, and wherein the plurality of braze preforms are each composed of a braze preform material comprising the parent superalloy and at least one melt point suppressant.

7. The turbine nozzle component of claim 6 wherein the braze preform material is substantially free of non-metallic components.

8. The turbine nozzle component of claim 1 wherein the braze preforms each comprise opposing sidewalls, which follow the contour of facing sidewalls of the plurality of nozzle vanes.

9. A turbine nozzle component, comprising:
a first endwall;
a second endwall radially spaced from the first endwall;
nozzle vanes extending between the first and second endwalls;
turbine nozzle flow paths extending through the turbine nozzle component and generally defined by the first endwall, the second endwall, and the nozzle vanes;
inter-blade flow areas provided on the first endwall between the nozzle vanes and partially bounding the turbine nozzle flow paths; and
braze preforms bonded to the first endwall to reduce the flow area of the turbine nozzle flow paths, the braze preforms having planform geometries substantially conformal with the inter-blade flow areas and each comprising:
an axially-elongated body; and
a leading portion having an increased lateral width as compared to the axially-elongated body, the leading portion wrapping around a leading edge of at least one of the nozzle vanes.

10. The turbine nozzle component of claim 9 wherein the first endwall, the second endwall, and the turbine nozzle vanes are cast as a single piece from a master superalloy.

11. The turbine nozzle component of claim 10 wherein the braze preforms are composed of a braze preform material comprising the master alloy and a melt point suppressant.

12. The turbine nozzle component of claim 10 wherein the braze preforms are composed of a braze preform material comprising the master alloy and boron.

13. The turbine nozzle component of claim 9 wherein the braze preforms are composed of multiple layers of sintered braze tape.

14. The turbine nozzle component of claim 9 wherein the braze preforms each further comprise:
a trailing portion having an increased lateral width as compared to the axially-elongated body, the trailing portion wrapping around a trailing edge of at least one of the nozzle vanes.

15. The turbine nozzle component of claim 9 wherein the braze preforms are resistance welded to the first endwall.

16. A turbine nozzle component, comprising:
a cast body, comprising:
a first endwall;
a second endwall radially spaced from the first endwall; and
nozzle vanes extending between the first and second endwalls, the nozzle vanes have a vane-to-vane spacing;

turbine nozzle flow paths extending through the cast body and each including a vane metering point having a radial height; and
a first plurality of braze preforms positioned within the turbine nozzle flow paths, bonded to the first endwall, and decreasing the radial heights of the vane metering points;
wherein the first plurality of braze preforms each comprise:
a curved body; and
at least one widened portion extending from the curved body and having a lateral width exceeding the vane-to-vane spacing.

17. The turbine nozzle component of claim 16 further comprising inter-blade flow areas provided on the first endwall between the nozzle vanes and covered, at least in substantial part, by the braze preforms.

18. The turbine nozzle component of claim 16 further comprising a second plurality of braze preforms positioned within the turbine nozzle flow paths, bonded to the second endwall, and further decreasing the radial heights of the vane metering points.

19. The turbine nozzle component of claim 16 wherein the curved body of each of the first plurality of braze preforms comprises opposing sidewalls, which follow the contour of facing sidewalls of the nozzle vanes.

Assignees

• Honeywell Int Inc

Inventors

• Macelroy Bill

Classifications

• F01D9/04 Primary

  forming ring or sector · CPC title

• F05D2230/237

  Brazing · CPC title

• F05D2230/21

  by casting · CPC title

• F05D2270/3061

  of the working fluid · CPC title

• F01D9/047 Primary

  Nozzle boxes · CPC title