Separable turbine vane stage

Patent metadata

Field	Value
Publication number	US-10774662-B2
Application number	US-201816037580-A
Country	US
Kind code	B2
Filing date	Jul 17, 2018
Priority date	Jul 17, 2018
Publication date	Sep 15, 2020
Grant date	Sep 15, 2020

Abstract

A vane stage segment is provided including an outer wall segment, an inner wall segment, and an airfoil. The outer wall segment is configured to be coupled to other outer wall segments to form an outer wall of the vane stage. The inner wall segment is spaced radially inward from the outer wall segment. At least one of the inner wall segment or the outer wall segment is separable between a forward portion and an aft portion. The airfoil extends between the outer wall segment and the inner wall segment.

First claim

What is claimed is:

1. A vane stage segment for use in a vane stage of a turbine engine, comprising:
an outer wall segment configured to be coupled to other outer wall segments to form an outer wall of the vane stage,
an inner wall segment spaced radially inward from the outer wall segment; and
an airfoil extending between the outer wall segment and the inner wall segment,
wherein at least one of the outer wall segment or the inner wall segment comprises:
a forward portion comprising a first interface and an aft portion comprising a second interface, the forward portion and the aft portion separably coupled to each other at the first and second interfaces;
a first portion flange radially extending from the forward portion;
a second portion flange radially extending from the aft portion; and
a fastener securing the first portion flange and the second portion flange together to form the separable coupling between the forward portion and the aft portion.

2. The vane stage segment of claim 1 , comprising a plurality of airfoils extending between the outer wall segment and the inner wall segment.

3. The vane stage segment of claim 1 , wherein the fastener is a bolt and nut.

4. The vane stage segment of claim 1 , wherein the outer wall segment comprises the forward portion and the aft portion separably coupled to each other.

5. The vane stage segment of claim 4 , wherein the forward portion comprises a first forward portion, the aft portion comprises a first aft portion, the fastener comprising a first fastener, the inner wall segment comprising:
a second forward portion comprising a third interface and a second aft portion comprising a fourth interface, the second forward portion and the second aft portion separably coupled each other at the third and fourth interfaces;
a third portion flange radially extending from the second forward portion;
a fourth portion flange radially extending from the second aft portion; and
a second fastener securing together the third flange portion and the fourth flange portion to form the separable coupling between the second forward portion and the second aft portion.

6. The vane stage segment of claim 1 , wherein the airfoil is separable from the outer wall segment and the inner wall segment.

7. The vane stage segment of claim 6 , wherein the airfoil comprises an outer endwall configured to be received within an opening formed in the outer wall segment, the outer endwall having a larger cross-sectional area than the airfoil.

8. The vane stage segment of claim 1 , wherein a forward portion of the vane stage segment is unitary body comprising the forward portion of the outer wall segment, the forward portion of the inner wall segment, and a forward portion of airfoil;
wherein an aft portion of the vane stage segment is unitary body comprising the aft portion of the outer wall segment, the aft portion of the inner wall segment, and an aft portion of the airfoil; and
the forward portion of the vane stage segment is configured to couple to the aft portion of the vane stage segment.

9. A vane stage for use in a turbine engine, comprising:
an outer wall comprising a plurality of outer wall segments coupled together circumferentially about a center of the vane stage, wherein each of the outer wall segments comprises an aft portion and a forward portion, and wherein for each of the outer wall segments, an associated forward portion is separably coupled to an associated aft portion by a fastener that is fastening together an associated set of portion flanges radially extending from the associated forward portion and the associated aft portion to form the separable coupling between the associated forward portion and the associated aft portion;
an inner wall spaced radially inward from the outer wall and extending circumferentially about the center of the vane stage; and
a plurality of airfoils spaced circumferentially about the center of the vane stage, each airfoil extending from the inner wall to the outer wall.

10. The vane stage of claim 9 , wherein each airfoil comprises an outer projection extending into one of the plurality of outer wall segments, wherein each airfoil is rotatable about the outer projection.

11. The vane stage of claim 10 , further comprising a control arm coupled to the outer projections of at least two of the airfoils, wherein the control arm is configured to coordinate the rotation of the airfoils coupled to the control arm.

12. The vane stage of claim 9 , wherein each airfoil comprises an outer endwall positioned within an opening formed in one of the outer wall segments wherein the outer endwall of each airfoil is rotatable within the opening.

13. The vane stage of claim 9 , wherein each outer wall segment is coupled to adjacent outer wall segments by a plurality of fasteners.

14. A method of manufacturing a vane stage for use in a turbine engine, comprising:
forming a plurality of outer wall segments by separably coupling a forward portion of each outer wall segment to an aft portion of each outer wall segment, wherein, for each outer wall segment, separably coupling the forward portion to the aft portion comprises fastening, with a fastener, a first flange radially extending from the forward portion to a second flange radially extending from the aft portion;
coupling an airfoil to each of the plurality of outer wall segments;
coupling the airfoil to an inner wall segment; and
forming an outer wall by coupling each of the outer wall segments to adjacent outer wall segments about a circumference of the vane stage.

15. The method of claim 14 , wherein the airfoil is at least partially made of a ceramic matrix composite.

16. The method of claim 15 , wherein each outer wall segment is made of a metal alloy.

17. The method of claim 16 , further comprising forming the plurality of wall segments by additive layer manufacturing.

18. The method of claim 16 , further comprising forming the plurality of wall segments by metal casting in a wax mold.

19. The method of claim 14 , further comprising coupling a control arm to the airfoil such that movement of the control arm rotates the airfoil.

Assignees

• Rolls Royce Corp

Inventors

• Brown Elise A M
• Mitchell Emma L
• Mcmillen Elyse M
• Tondreau Iii David L
• Koenig Eric T
• Taketa Linnea L

Classifications

• F05D2230/60

  Assembly methods · CPC title

• F05D2300/175

  Superalloys · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F01D9/042 Primary

  fixing blades to stators (fixing stator-rings in the casing or to each other F01D25/246) · CPC title

• F05D2300/174

  Titanium alloys, e.g. TiAl · CPC title