Shroud assembly and shroud for gas turbine engine
AssigneeGeneral Electric Company
InventorDavid Scott Stapleton
Life of this patent
Estimating the term…
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.
Claims12
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.
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.
Dependencies are inferred from the claim text.