Blisk bonded CMC airfoil having attachment

Patent metadata

Field	Value
Publication number	US-11268389-B2
Application number	US-201815978807-A
Country	US
Kind code	B2
Filing date	May 14, 2018
Priority date	May 14, 2018
Publication date	Mar 8, 2022
Grant date	Mar 8, 2022

Abstract

A turbine blade is secured with a turbine disk by a retention assembly. The turbine blade includes a blade stem and the disk includes at least one mount post for mounting of the turbine blade. The retention assembly is secured with the disk by forming a diffusion joint with the disk.

First claim

What is claimed is:

1. An airfoil assembly of a gas turbine engine, the airfoil assembly comprising:
at least one blade including a blade body formed to have an airfoil and a root having a blade stem extending from the blade body for securing the at least one blade;
a disk including a disk body and at least one mount post extending radially from the disk body for mounting of the at least one blade; and
a blade retention assembly for securing the at least one blade to the disk, the blade retention assembly including a clamp block formed to define a stem cavity for receiving the blade stem, the clamp block being arranged about the blade stem and joined with the at least one mount post of the disk by a diffusion joint formed between the at least one mount post and the clamp block, the at least one mount post including a radially outermost surface for engagement with a radially inward facing bottom surface of the clamp block,
wherein the radially inward facing bottom surface of the clamp bock defines an axial-circumferential plane that extends in an axial direction and in a circumferential direction,
wherein the clamp block includes a mounting base including the radially inward facing bottom surface for engagement with the radially outermost surface of the at least one mount post to form the diffusion joint, the radially inward facing bottom surface of the clamp block including at least a portion that extends continuously from an axially foremost edge of the clamp block to an axially aftmost edge of the clamp block in the axial-circumferential plane, and
wherein the clamp block includes a first form extending circumferentially away from a first circumferentially-facing outer sidewall of the clamp block and a second form extending circumferentially away from a second circumferentially-facing outer sidewall opposite the first circumferentially-facing outer sidewall, the first form and the second form defining a flow path surface, and each of the first form and the second form including a beveled end on an underside corner of a lateral end of the form.

2. The airfoil assembly of claim 1 , wherein the clamp block includes at least two block sections, each block section including a clamp receptacle defined in the block section to collectively form the stem cavity.

3. The airfoil assembly of claim 2 , wherein each clamp receptacle is defined at least partly by an engagement surface, the engagement surface angled to face radially inward.

4. The airfoil assembly of claim 3 , wherein the blade stem includes a pair of dovetail surfaces angled to face radially outward for engagement with the engagement surface of at least one of the block sections.

5. The airfoil assembly of claim 3 , wherein each engagement surface extends continuously from an axially foremost edge of the clamp receptacle to an axially aftmost edge of the clamp receptacle.

6. The airfoil assembly of claim 1 , wherein each block section forms a portion of the mounting base.

7. The airfoil assembly of claim 1 , wherein one of the at least one mount post and the mounting base defines a receptacle for insertion of at least a portion of the other of the at least one mount post and the mounting base.

8. The airfoil assembly of claim 1 , wherein the at least one mount post is formed as a protrusion extending radially from an outer surface of the disk body to define a height.

9. The airfoil assembly of claim 1 , wherein the diffusion joint includes a number of diffusion-brazed bonds.

10. The airfoil assembly of claim 9 , wherein at least one of the number of diffusion-brazed bonds is radially oriented.

11. The airfoil assembly of claim 1 , wherein the stem cavity defines a radially inwardmost cavity bottom surface that extends continuously from an axially foremost edge of the stem cavity to an axially aftmost edge of the stem cavity in a second plane that is parallel to the axial-circumferential plane.

12. The airfoil assembly of claim 11 , wherein the at least one blade defines a radially inwardmost blade bottom surface that extends continuously from an axially foremost edge of the at least one blade to an axially aftmost edge of the at least one blade in a third plane that is parallel to the axial-circumferential plane.

13. A turbine section of a gas turbine engine, the turbine section comprising:
at least one blade including a blade body formed to have a turbine airfoil and a root having a blade stem extending from the blade body for securing the at least one blade;
a turbine disk including a disk body and at least one mount post extending radially from the disk body for mounting of the at least one blade; and
a blade retention assembly for securing the at least one blade to the turbine disk, the blade retention assembly including a clamp block formed to define a stem cavity for receiving the blade stem, the clamp block being arranged about the blade stem and joined with the at least one mount post of the turbine disk by a diffusion joint formed between the at least one mount post and the clamp block, the at least one mount post including a radially outermost surface for engagement with a radially inward facing bottom surface of the clamp block,
wherein the radially inward facing bottom surface of the clamp bock defines an axial-circumferential plane that extends in an axial direction and in a circumferential direction,
wherein the clamp block includes a mounting base including the radially inward facing bottom surface for engagement with the radially outermost surface of the at least one mount post to form the diffusion joint, the radially inward facing bottom surface of the clamp block including at least a portion that extends continuously from an axially foremost edge of the clamp block to an axially aftmost edge of the clamp block in the axial-circumferential plane,
wherein the clamp block includes at least two block sections, each block section including a clamp receptacle defined in the block section to collectively form the stem receptacle, each clamp receptacle is defined by a generally circumferentially-facing surface, a first axially-facing surface, and a second axially-facing surface opposite the first axially-facing surface, and
wherein an isolation barrier is disposed between an outer surface of the blade stem and each of the first axially-facing surface, the second axially-facing surface, and the generally circumferentially-facing surface of each clamp receptacle; the isolation barrier being an anti-diffusion layer configured to obstruct diffusion bonding between the outer surface of the blade stem and the clamp receptacles.

14. The turbine section of claim 13 , wherein each block section forms a portion of the mounting base.

15. The turbine section of claim 13 , wherein the generally circumferentially-facing surface of each clamp receptacle is an engagement surface, the engagement surface angled to face radially inward.

16. The turbine section of claim 15 , wherein the blade stem includes a pair of dovetail surfaces angled to face radially outward for engagement with the engagement surface of at least one of the block sections.

17. The turbine section of claim 13 , wherein the at least one mount post is formed as a protrusion extending radially from an outer surface of the disk body to define a height.

18. A method of assembling an airfoil of a gas turbine engine, the method comprising:
arranging a blade stem of a blade within a stem cavity of a clamp block of a retention assembly, the clamp block including a protrusion extending radially inwardly away from a bottom surface of the clamp block, t

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Freeman Ted J
• Sippel Aaron D
• Varney Bruce E

Classifications

• F01D5/3084

  the blades being made of ceramics · CPC title

• B23K1/0018 Primary

  Brazing of turbine parts · CPC title

• F01D5/3007

  of axial insertion type · CPC title

• F05D2230/237

  Brazing · CPC title

• F01D5/3023

  of radial insertion type, e.g. in individual recesses · CPC title