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US 10,760,494 B2Granted
Telescoping bore basket for gas turbine engine
AssigneeRaytheon Technologies Corporation
InventorsKonstantinos Panagiotis Giannakopoulos, Andrew C. Carmack, Mohammad G. Faisal
Life of this patent
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Abstract
A bore basket assembly for a gas turbine engine. The assembly includes an outer cylindrical member. The assembly also includes an inner cylindrical member at least partially surrounded by the outer cylindrical member to define an annulus therebetween, one of the cylindrical members operatively coupled to an aft rotor stage, the other of the cylindrical members operatively coupled to a forward rotor stage, the cylindrical members moveable in an axially telescoping manner relative to each other.
Claims20
A bore basket assembly for a gas turbine engine comprising:
- an outer cylindrical member;
- a plurality of radial openings located in the outer cylindrical member;
- an inner cylindrical member at least partially surrounded by the outer cylindrical member to define an annulus therebetween, one of the cylindrical members operatively coupled to an aft rotor stage, the other of the cylindrical members operatively coupled to a forward rotor stage, the inner cylindrical member and the outer cylindrical member moveable in an axially telescoping manner with respect to each other;
- and
- a flange extending radially outward from the inner cylindrical member, the flange defining a plurality of circumferentially spaced flow slots between the outer cylindrical member and the inner cylindrical member, the plurality of circumferentially spaced flow slots providing fluid communication between the annulus and a bleed port, the bleed port being located in the forward rotor stage.
2 more elements
A gas turbine engine comprising:
- a compressor section;
- a combustor section;
- a turbine section;
- and
- a bore basket assembly disposed in the compressor section, the bore basket assembly comprising:
- an outer cylindrical member;
- and
- a plurality of radial openings located in the outer cylindrical member;
- an inner cylindrical member surrounding a portion of a shaft operatively coupling the turbine section and the compressor section, the inner cylindrical member at least partially surrounded by the outer cylindrical member to define an annulus therebetween, one of the cylindrical members operatively coupled to an aft rotor stage, the other of the cylindrical members operatively coupled to a forward rotor stage, the inner cylindrical member and the outer cylindrical member moveable in an axially telescoping manner with respect to each other;
- and
- a flange extending radially outward from the inner cylindrical member, the flange defining a plurality of circumferentially spaced flow slots between the outer cylindrical member and the inner cylindrical member, the plurality of circumferentially spaced flow slots providing fluid communication between the annulus and a bleed port, the bleed port being located in the forward rotor stage.
8 more elements
A method of cooling a portion of a gas turbine engine, comprising:
- locating a bore basket assembly in a compressor section of the gas turbine engine, the bore basket assembly comprising;
- an outer cylindrical member, a plurality of radial openings located in the outer cylindrical member;
- an inner cylindrical member surrounding a portion of a shaft operatively coupling the turbine section and the compressor section, the inner cylindrical member at least partially surrounded by the outer cylindrical member to define an annulus therebetween, the inner cylindrical member and the outer cylindrical member moveable in an axially telescoping manner with respect to each other, and a flange extending radially outward from the inner cylindrical member, the flange defining a plurality of circumferentially spaced flow slots between the outer cylindrical member and the inner cylindrical member, the plurality of circumferentially spaced flow slots providing fluid communication between the annulus and a bleed port, the bleed port being located in the forward rotor stage;
- and
- directing a cooling flow through the annulus by first passing the cooling into the plurality of radial openings and then through the plurality of circumferentially spaced flow slots in order to provide the cooling flow to the bleed port, wherein the plurality of radial openings are adjacent to an aft end of the bore basket assembly and the plurality of circumferentially spaced flow slots are located adjacent to a forward end of the bore basket assembly.
2 more elements
Dependencies are inferred from the claim text.