Gas turbine engine components having sealed stress relief slots and methods for the fabrication thereof

Patent metadata

Field	Value
Publication number	US-9506365-B2
Application number	US-201414257485-A
Country	US
Kind code	B2
Filing date	Apr 21, 2014
Priority date	Apr 21, 2014
Publication date	Nov 29, 2016
Grant date	Nov 29, 2016

Abstract

Embodiments of a gas turbine engine component having sealed stress relief slots are provided, as are embodiments of a gas turbine engine containing such a component and embodiments of a method for fabricating such a component. In one embodiment, the gas turbine engine includes a core gas flow path, a secondary cooling flow path, and a turbine nozzle or other gas turbine engine component. The component includes, in turn, a component body through which the core gas flow path extends, a radially-extending wall projecting from the component body and into the secondary cooling flow path, and one or more stress relief slots formed in the radially-extending wall. The stress relief slots are filled with a high temperature sealing material, which impedes leakage between the second cooling and core gas flow paths and which fractures to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.

First claim

What is claimed is:

1. A gas turbine engine, comprising:
a core gas flow path;
a secondary cooling flow path; and
a gas turbine engine component, comprising:
a component body through which the core gas flow path extends;
a radially-extending wall projecting from the component body into the secondary cooling flow path;
one or more stress relief slots formed in the radially-extending wall and having interior surfaces; and
a high temperature braze material infiltrated into the one or more stress relief slots and bonded to the interior surfaces thereof, the high temperature braze material impeding leakage between the secondary cooling flow path and the core gas flow path, and fracturing to alleviate thermomechanical stress within the radially-extending wall during operation of the gas turbine engine.

2. The gas turbine engine of claim 1 wherein the gas turbine engine component comprises a turbine nozzle, and wherein the component body comprises:
an inner endwall;
an outer endwall circumscribing the inner endwall; and
a plurality of circumferentially-spaced vanes extending between the inner and outer endwalls.

3. The gas turbine engine of claim 2 wherein the radially-extending wall comprises a rail projecting radially outward from an edge portion of the outer endwall.

4. The gas turbine engine of claim 3 wherein the rail has a generally annular shape and extends around the edge portion of the gas turbine engine, and wherein the one or more stress relief slots comprise a plurality of stress relief slots spaced around the rail at substantially regular intervals.

5. The gas turbine engine of claim 4 wherein the rail and the outer endwall are integrally formed as a single piece.

6. The gas turbine engine of claim 2 wherein the rail comprises an annular sealing surface, and wherein the gas turbine engine further comprises:
static engine infrastructure to which the rail is attached; and
an annular compression seal disposed between the static engine infrastructure and the sealing surface of the rail, the one or more stress relief slots extending through the sealing surface of the rail.

7. The gas turbine engine of claim 6 wherein the one or more stress relief slots extend radially inboard the annular compression seal.

8. The gas turbine engine of claim 1 wherein the one or more stress relief slots have a substantially constant width.

9. The gas turbine engine of claim 1 wherein the stress relief slots each have a generally J-shaped geometry.

10. The gas turbine engine of claim 1 wherein the high temperature braze material comprises a nickel-based braze material.

11. A gas turbine engine component for usage within in a gas turbine engine having a core gas flow path and a secondary cooling flow path, the gas turbine engine component comprising:
a component body having a radially-extending wall projecting therefrom, the component body and the radially-extending wall exposed to the core gas flow path and to the secondary cooling flow path, respectively, when the gas turbine engine component is installed within the gas turbine engine;
a plurality of stress relief slots extending axially through the radially-extending wall and having interior slot surfaces; and
a high temperature sealing material melted over and bonded to the interior slot surfaces and filling the plurality of stress relief slots, the high temperature sealing material impeding leakage across the radially-extending wall, the high temperature sealing material fracturing to alleviate thermomechanical stress when a temperature differential develops across the radially-extending wall.

12. The gas turbine engine component of claim 11 wherein the component body comprises:
an inner endwall;
an outer endwall circumscribing the inner endwall; and
a plurality of circumferentially-spaced vanes extending between the inner and outer endwalls.

13. The gas turbine engine component of claim 12 wherein the first radially-extending wall comprises a rail extending form an edge portion of the outer endwall.

14. The gas turbine engine component of claim 13 wherein the rail comprises an annular sealing surface through which the plurality of stress relief slots extend.

15. The gas turbine engine component of claim 11 wherein the high temperature sealing material comprises a nickel-based braze material.

16. A method for fabricating a gas turbine engine component utilized within a gas turbine engine having a core gas flow path and a secondary flow path, the method comprising:
obtaining a component body having a radially-extending wall projecting therefrom;
forming a plurality of stress relief slots in the radially-extending wall; and
filling the plurality of stress relief slots with a high temperature sealing material impeding leakage across the radially-extending wall between the second cooling flow path and the core gas flow path, the high temperature sealing material selected to have a mechanical strength less the parent material of the radially-extending wall such that the high temperature sealing material fractures preferentially to relieve thermomechanical stress when a temperature gradient develops across the radially-extending wall during usage of the turbine nozzle;
wherein filling comprises:
disposing a braze material adjacent the plurality of stress relief slots; and
heating the braze material to a sufficient temperature to bond the braze material to surfaces of the radially-extending wall defining the plurality of stress relief slots.

17. The method of claim 16 wherein disposing comprises dispensing the braze material over the stress relief slots in liquid form.

18. The method of claim 16 wherein disposing comprises inserting flexible strips of braze foil into the plurality of stress relief slots.

19. The method of claim 16 wherein the component body comprises an outer endwall, wherein the first radially-extending wall comprises a rail projecting from radially outward from an edge portion of the outer endwall, and wherein forming comprises cutting the plurality of stress relief slots into the rail.

Assignees

• Honeywell Int Inc

Inventors

• Smoke Jason
• Tucker Bradley Reed
• Riahi Ardeshir
• Zurmehly Ed
• Mirzamoghadam Alexander

Classifications

• F01D9/041

  using blades (F01D5/148 takes precedence) · CPC title

• F01D25/12

  Cooling · CPC title

• F05D2260/941

  particularly aimed at mechanical or thermal stress reduction · CPC title

• B22D25/02

  by its peculiarity of shape; of works of art {(cylinders, pistons B22D15/02)} · CPC title

• B22D25/06

  by its physical properties (B22D27/00 takes precedence) · CPC title