Shroud assembly and shroud for gas turbine engine

Patent metadata

Field	Value
Publication number	US-9863265-B2
Application number	US-201514686800-A
Country	US
Kind code	B2
Filing date	Apr 15, 2015
Priority date	Apr 15, 2015
Publication date	Jan 9, 2018
Grant date	Jan 9, 2018

Abstract

Shroud assemblies and shrouds for gas turbine engines are provided. A shroud includes a shroud body which includes a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface. The shroud further includes a forward flange extending from the outer surface of the shroud body, and a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange. The shroud further includes a rib disposed between and in contact with the forward flange and the rear flange.

First claim

What is claimed is:

1. A shroud assembly for a gas turbine engine, the shroud assembly comprising:
a hanger, the hanger comprising a forward hanger arm, a rear hanger arm axially spaced from the forward hanger arm, a hanger body extending between the forward hanger arm and the rear hanger arm, and a flange extending from the hanger body, the hanger further comprising a bore hole defined in the flange;
a shroud, the shroud comprising:
a shroud body comprising a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface;
a forward flange extending from the outer surface of the shroud body, the forward flange defining a bore hole;
a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange, the rear flange defining a bore hole; and
a rib disposed between and in contact with the forward flange and the rear flange; the rib comprising a plurality of plies stacked in a radial direction, wherein each ply of the plurality of plies is substantially parallel to the shroud body outer surface; and

a pin extending through the bore hole of the hanger and at least one of the bore hole of the forward flange or the bore hole of the rear flange,
wherein the shroud body, the forward flange, the rear flange, and the rib are formed from a ceramic matrix composite material.

2. The shroud assembly of claim 1 , wherein the rib extends axially between the forward flange and the rear flange, and wherein the plurality of plies comprises continuous plies or discontinuous plies.

3. The shroud assembly of claim 2 , wherein the rib defines a radially extending height and a length extending between the forward flange and the rear flange, and wherein the height is generally constant throughout the entire length.

4. The shroud assembly of claim 1 , wherein the rib defines a radially extending height and a length extending between the forward flange and the rear flange, and wherein the height tapers from at least one of the forward flange and the rear flange through at least a portion of the length.

5. The shroud assembly of claim 3 , wherein the rib comprises a plurality of ribs.

6. The shroud assembly of claim 5 , wherein each of the plurality of ribs is generally circumferentially spaced from others of the plurality of ribs.

7. The shroud assembly of claim 6 , wherein each of the plurality of ribs defines a radially extending height, and wherein the height of at least one of the plurality of ribs is greater than the height of at least another of the plurality of ribs.

8. A gas turbine engine, comprising:
a compressor;
a combustion section;
a turbine; and
a shroud disposed in one of the compressor or the turbine, the shroud comprising:
a shroud body comprising a forward surface, a rear surface axially spaced from the forward surface, an inner surface extending between the forward surface and the rear surface, and an outer surface extending between the forward surface and the rear surface and radially spaced from the inner surface;
a forward flange extending from the outer surface of the shroud body;
a rear flange extending from the outer surface of the shroud body, the rear flange axially spaced from the forward flange; and
a rib disposed between and in contact with the forward flange and the rear flange, the rib comprising a plurality of plies stacked in a radial direction, wherein each ply of the plurality of plies is substantially parallel to the shroud body outer surface,
wherein the rib is radially spaced a distance away from the shroud body outer surface.

9. The gas turbine of claim 8 , wherein the rib extends axially between the forward flange and the rear flange.

10. The gas turbine of claim 8 , wherein the rib defines a radially extending height and a length extending between the forward flange and the rear flange, and wherein the height is generally constant through the entire length.

11. The gas turbine of claim 8 , wherein the rib comprises a plurality of ribs.

12. The gas turbine of claim 11 , wherein each of the plurality of ribs is generally circumferentially spaced from others of the plurality of ribs.

Assignees

• Gen Electric

Inventors

• Stapleton David Scott

Classifications

• F01D25/246

  Fastening of diaphragms or stator-rings · CPC title

• F01D9/04 Primary

  forming ring or sector · CPC title

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• F05D2240/11

  Shroud seal segments · CPC title

• F04D29/321

  for axial flow compressors · CPC title