Pin supported CMC shroud

Patent metadata

Field	Value
Publication number	US-10024193-B2
Application number	US-201514945789-A
Country	US
Kind code	B2
Filing date	Nov 19, 2015
Priority date	Nov 19, 2015
Publication date	Jul 17, 2018
Grant date	Jul 17, 2018

Abstract

The present disclosure is directed to a component for a gas turbine. The component includes a component wall having a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface. A first boss extends radially outwardly from the radially outer surface, includes a first circumferentially outer surface, and defines a first aperture extending axially therethrough. A second boss extends radially outwardly from the radially outer surface and is circumferentially spaced apart from the first boss. The second boss includes a second circumferentially outer surface and defines a second aperture extending axially therethrough. The first circumferentially outer surface of the first boss and the second circumferentially outer surface of the second boss form a pair of angles with respect to the radially inner surface.

First claim

What is claimed is:

1. A component for a gas turbine, comprising:
a component wall comprising a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface;
a first boss extending radially outwardly from the radially outer surface, wherein the first boss comprises a first circumferentially outer surface and defines a first aperture extending axially therethrough; and
a second boss extending radially outwardly from the radially outer surface and circumferentially spaced apart from the first boss, wherein the second boss comprises a second circumferentially outer surface and defines a second aperture extending axially therethrough,
wherein the first circumferentially outer surface of the first boss is circumferentially aligned and parallel to the first circumferential surface of the component wall to form a first continuous surface and the second circumferentially outer surface of the second boss is circumferentially aligned and parallel to the second circumferential surface of the component wall to form a second continuous surface;
wherein the component is a shroud.

2. The component of claim 1 , wherein the component wall, the first boss, and the second boss are constructed from a composite.

3. The component of claim 1 , wherein the first circumferentially outer surface and the second circumferentially outer surface are planar.

4. The component of claim 1 , further comprising:
a fillet that couples the radially outer surface to a circumferentially inner surface of the first boss or the second boss.

5. A component for a gas turbine, comprising:
a component wall comprising a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface;
a first boss extending radially outwardly from the radially outer surface, wherein the first boss comprises a first circumferentially outer surface and defines a first aperture extending axially therethrough; and
a second boss extending radially outwardly from the radially outer surface and circumferentially spaced apart from the first boss, wherein the second boss comprises a second circumferentially outer surface and defines a second aperture extending axially therethrough,
wherein the first circumferentially outer surface of the first boss is parallel to the first circumferential surface of the component wall to form a first continuous surface and the second circumferentially outer surface of the second boss is parallel to the second circumferential surface of the component wall to form a second continuous surface;
wherein the component is a shroud; and
wherein the first boss or the second boss comprises a first boss portion and a second boss portion axially spaced apart from the first boss portion.

6. A gas turbine, comprising:
a compressor;
a combustion section;
a turbine;
a shaft rotatably coupling the compressor and the turbine; and
a shroud positioned in the turbine or the compressor, the shroud comprising:
a shroud wall comprising a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface;
a first boss extending radially outwardly from the radially outer surface, wherein the first boss comprises a first circumferentially outer surface and defines a first aperture extending axially therethrough; and
a second boss extending radially outwardly from the radially outer surface and circumferentially spaced apart from the first boss, wherein the second boss comprises a second circumferentially outer surface and defines a second aperture extending axially therethrough,

wherein the first circumferentially outer surface of the first boss is circumferentially aligned and parallel to the first circumferential surface of the component wall to form a first continuous surface and the second circumferentially outer surface of the second boss is circumferentially aligned and parallel to the second circumferential surface of the component wall to form a second continuous surface.

7. The gas turbine of claim 6 , wherein the shroud wall, the first boss, and the second boss are constructed from a composite.

8. The gas turbine of claim 6 , wherein the first circumferentially outer surface and the second circumferentially outer surface are planar.

9. The gas turbine of claim 6 , wherein the shroud comprises a fillet that couples the radially outer surface to a circumferentially inner surface of the first boss or the second boss.

10. The gas turbine of claim 6 , wherein the shroud further comprises a first shroud and a second shroud axially aligned with and circumferentially adjacent to the first shroud.

11. The gas turbine of claim 10 , wherein the first circumferentially outer surface of the first boss of the second shroud is positioned circumferentially between the first circumferential surface of the second shroud and the second circumferential surface of the first shroud.

12. A gas turbine, comprising:
a compressor;
a combustion section;
a turbine;
a shaft rotatably coupling the compressor and the turbine; and
a shroud positioned in the turbine or the compressor, the shroud comprising:
a shroud wall comprising a radially inner surface, a radially outer surface, a first circumferential surface, and a second circumferential surface;
a first boss extending radially outwardly from the radially outer surface, wherein the first boss comprises a first circumferentially outer surface and defines a first aperture extending axially therethrough; and
a second boss extending radially outwardly from the radially outer surface and circumferentially spaced apart from the first boss, wherein the second boss comprises a second circumferentially outer surface and defines a second aperture extending axially therethrough,
wherein the first circumferentially outer surface of the first boss is parallel to the first circumferential surface of the component wall to form a first continuous surface and the second circumferentially outer surface of the second boss is parallel to the second circumferential surface of the component wall to form a second continuous surface;

wherein the shroud further comprises a first shroud and a second shroud axially aligned with and circumferentially adjacent to the first shroud;
wherein the first circumferentially outer surface of the first boss of the second shroud is positioned circumferentially between the first circumferential surface of the second shroud and the second circumferential surface of the first shroud; and
wherein the first boss of the second shroud comprises a first boss portion and a second boss portion axially spaced apart from the first boss portion, and wherein the second boss of the first shroud is positioned axially between the first boss portion and the second boss portion.

13. A method for fabricating a composite component for a gas turbine, the method comprising:
laying a first plurality of composite plies in a mold, wherein a portion of the first plurality of composite plies curves radially outward;
laying a second plurality of composite plies over the first plurality of composite plies, wherein a first portion of the second plurality of composite plies contacts the first plurality of composite plies, and a second portion of the second plurality of composite plies extends past the portion of the first plurality of composite plies;
folding the second portion of the second plurality of composite plies over the first portion of the second plurality of composite plies;
curing the first plurality of composite plies and the second plurality of composite plies; and
machining the first p

Assignees

• Gen Electric

Inventors

• Shapiro Jason David

Classifications

• B29L2031/7504

  Turbines · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2260/30

  Retaining components in desired mutual position · CPC title

• F04D29/545

  Ducts · CPC title

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title