Turbine blade squealer tip including internal squealer tip cooling channel

Patent metadata

Field	Value
Publication number	US-11655717-B2
Application number	US-202016951947-A
Country	US
Kind code	B2
Filing date	Nov 18, 2020
Priority date	May 7, 2018
Publication date	May 23, 2023
Grant date	May 23, 2023

Abstract

A gas turbine engine component may include an airfoil extending radially from a base to a blade tip, the airfoil including a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge, an internal cooling circuit extending from the base to the blade tip; and a squealer tip. The squealer tip may include a first and a second squealer tip rail adjacent to the first squealer tip rail, and a squealer tip cap extending between the first and second squealer tip rails. The blade tip, the first and second squealer tip rails, and the squealer tip cap may define an internal squealer tip cooling channel. The blade tip may define a supply aperture that fluidly connect the internal cooling circuit and the internal squealer tip cooling channel.

First claim

What is claimed is:

1. A method of forming a gas turbine engine component, the method comprising:
providing an airfoil extending radially from a base to a blade tip, wherein the airfoil comprises:
a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge; and
an internal cooling circuit extending from the base to the blade tip;

forming a presintered preform comprising:
a first squealer tip rail;
a second squealer tip rail adjacent to the first squealer tip rail; and
a squealer tip cap extending between the first and second squealer tip rails;

disposing, before brazing the presintered preform to the blade tip, a filler material between the first and second squealer tip rails; and
brazing the presintered preform to the blade tip, wherein the blade tip, the first and second squealer tip rails, and the squealer tip cap define an internal squealer tip cooling channel, and wherein the blade tip defines a supply aperture that fluidly connects the internal cooling circuit and the internal squealer tip cooling channel.

2. The method of claim 1 , wherein the method further comprises machining material from the blade tip.

3. The method of claim 1 , wherein the method further comprises forming the supply aperture in the blade tip.

4. The method of claim 1 , wherein the presintered preform comprises a wide gap braze composition.

5. The method of claim 1 , wherein the presintered preform comprises particles of an abrasive.

6. The method of claim 1 , wherein the method further comprises forming in at least a portion of the blade tip one or more three-dimensional features, wherein the one or more three-dimensional features are configured to increase a convective heat transfer from the blade tip to a cooling fluid inside the internal squealer tip cooling channel.

7. The method of claim 1 , wherein forming the presintered preform further comprises forming in at least a portion of at least one of the first squealer tip rail or the second squealer tip rail one or more three-dimensional features, wherein the one or more three-dimensional features are configured to increase a convective heat transfer from the at least one of the first squealer tip rail or the second squealer tip rail to a cooling fluid inside the internal squealer tip cooling channel.

8. The method of claim 1 , wherein filler material comprises at least one of a metal oxide, yttrium oxide, or aluminium oxide and a binder.

9. The method of claim 1 , wherein the filler material comprises at least one of a refractor metal or molybdenum.

10. The method of claim 1 , further comprising removing, by at least one of heating or chemical etching, the filler material.

11. The method of claim 1 , wherein brazing the presintered preform to the blade tip further comprises induction heating of at least a portion of the presintered preform.

12. The method of claim 1 , wherein brazing the presintered preform to the blade tip further comprises heating within a vacuum furnace at least the blade tip and the presintered preform.

13. The method of claim 1 , wherein the method further comprises, after brazing the presintered preform to the blade tip, machining excess material from at least one of first squealer tip rail, the second squealer tip rail, or the squealer tip cap.

14. The method of claim 1 , wherein the method further comprises applying an abrasive coating to a surface of the squealer tip cap.

15. A method of forming a gas turbine engine component, the method comprising:
providing an airfoil extending in a radial direction from a base to a blade tip, wherein the airfoil comprises:
a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge; and
an internal cooling circuit extending from the base to the blade tip;

forming a presintered preform comprising:
a first squealer tip rail;
a second squealer tip rail adjacent to the first squealer tip rail; and
a squealer tip cap extending between the first and second squealer tip rails, the squealer tip cap being further in the radial direction from the blade tip than the first squealer tip rail and the second squealer tip rail; and

brazing the presintered preform to the blade tip,
wherein the blade tip, the first and second squealer tip rails, and the squealer tip cap define an internal squealer tip cooling channel, wherein, after brazing the presintered preform to the blade tip, the blade tip defines a supply aperture that fluidly connects the internal cooling circuit and the internal squealer tip cooling channel, and wherein at least one of the first squealer tip rail or the second squealer tip rail includes a discharge aperture defining a discharge flow path from the internal squealer tip cooling channel to an environment external to the airfoil and the presintered preform.

16. The method of claim 15 , further comprising applying an abrasive coating to an outmost surface in the radial direction of the squealer tip cap.

17. The method of claim 15 , wherein the internal cooling circuit of the airfoil is fluidically connected to the discharge aperture via the internal squealer tip cooling channel such that a fluid within the internal cooling circuit of the airfoil flows out of the discharge aperture via the internal squealer tip cooling channel to the environment external to the airfoil and the presintered preform.

18. The method of claim 15 , wherein, after brazing the presintered preform to the blade tip, the squealer tip cap defines an outermost surface in the radial direction from the base of the gas turbine engine component.

19. The method of claim 15 , further comprising machining material from the blade tip.

20. The method of claim 15 , further comprising forming the supply aperture in the blade tip.

Assignees

• Rolls Royce Corp

Inventors

• Henderkott Joseph Peter
• Moga Corina
• Weaver John Alan
• Wood Michael

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• F05D2230/22

  by sintering · CPC title

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• F01D5/20 Primary

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F01D5/187 Primary

  Convection cooling · CPC title