Gas turbine engine exhaust case with blade shroud and stiffeners
AssigneePratt & Whitney Canada Corp.
InventorsPhilippe Savard, Guy Lefebvre
Life of this patent
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Abstract
An assembly is provided for a gas turbine engine. This engine assembly includes a bladed rotor rotatable about an axis, and an engine case. The engine case includes an outer duct wall, a first circumferential stiffener, a second circumferential stiffener and a plurality of axial stiffeners. The outer duct wall forms a shroud around the bladed rotor. The first circumferential stiffener extends circumferentially about the outer duct wall. The second circumferential stiffener extends circumferentially about the outer duct wall. The axial stiffeners are arranged circumferentially about the outer duct wall. Each of the axial stiffeners extends axially between the first circumferential stiffener and the second circumferential stiffener.
Claims20
An assembly for a gas turbine engine, comprising:
- a bladed rotor rotatable about an axis;
- and
- an engine case including an outer duct wall, a first circumferential stiffener, a second circumferential stiffener and a plurality of axial stiffeners, the outer duct wall forming a shroud around the bladed rotor, the first circumferential stiffener extending circumferentially about the outer duct wall, the second circumferential stiffener extending circumferentially about the outer duct wall, the plurality of axial stiffeners arranged circumferentially about the outer duct wall, and each of the plurality of axial stiffeners extending axially between the first circumferential stiffener and the second circumferential stiffener.
An assembly for a gas turbine engine, comprising:
- an exhaust outer duct wall extending circumferentially around and axially along an axis;
- a first circumferential stiffener projecting radially out from and circumscribing the exhaust outer duct wall;
- a second circumferential stiffener projecting radially out from and circumscribing the exhaust outer duct wall;
- and
- a plurality of axial stiffeners arranged circumferentially about the axis in an array, each of the plurality of axial stiffeners projecting radially out from the exhaust outer duct wall, and each of the plurality of axial stiffeners extending axially between the first circumferential stiffener and the second circumferential stiffener.
An assembly for a gas turbine engine, comprising:
- a turbine section;
- an exhaust section;
- and
- an engine case forming a peripheral boundary of an engine flowpath within at least one of the turbine section or the exhaust section, the engine case comprising a first circumferential stiffener, a second circumferential and a plurality of axial stiffeners arranged in a circular array, each of the plurality of axial stiffeners extending axially between and formed integral with the first circumferential stiffener and the second circumferential stiffener.
Dependencies are inferred from the claim text.