ANTI-VORTEX DEVICE FOR A GAS TURBINE ENGINE COMPRESSOR
First Claim
1. A compressor rotor assembly mounted for rotation about a central axis of a gas turbine engine, comprising an anti-vortex device having a peripheral rim surface defining an inner boundary of a primary gas path of the engine, the anti-vortex device defining circumferentially spaced-apart radial passageways extending from respective axially extending central passages to an outer peripheral rim surface of the device, each said radial passageway receiving bleed air from the primary gas path and directing it to an associated one of said axially extending passages.
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Accused Products
Abstract
An anti-vortex device for use in a compressor rotor assembly of a gas turbine engine is described. Spaced-apart radial passageways extend from an axially extending passage provided in a central area of the device to an outer peripheral rim surface thereof. The radial passageways channel air from the primary gaspath about the rotor assembly to the axially extending passage where the air is directed into a central axial passage of the rotor assembly.
18 Citations
19 Claims
- 1. A compressor rotor assembly mounted for rotation about a central axis of a gas turbine engine, comprising an anti-vortex device having a peripheral rim surface defining an inner boundary of a primary gas path of the engine, the anti-vortex device defining circumferentially spaced-apart radial passageways extending from respective axially extending central passages to an outer peripheral rim surface of the device, each said radial passageway receiving bleed air from the primary gas path and directing it to an associated one of said axially extending passages.
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10. A gas turbine engine comprising a compressor having at least two rotors mounted for joint rotation about a central axis, a combustor and a turbine section;
- the compressor has an anti-vortex device secured between said at least two rotors, the anti-vortex device having a solid body portion, circumferentially spaced-apart radial passageways defined in said solid body portion, each said radial passageway extending from an axial passage extending through the solid body portion in a central area thereof to an outer peripheral rim surface of the solid body portion, the outer peripheral rim surface being spaced inwardly of an air bleed gap formed between said at least two rotors and in communication with a gaspath of the engine, the anti-vortex device channelling air from the gaspath in non-interference therewith through said air bleed gap and into said radial passageways and said axial passage, said axial passage redirecting said air under pressure in two opposite axial directions.
- View Dependent Claims (11, 12, 13, 14)
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15. A method of reducing total pressure drop and the formation of free vortex in a flow of compressed air bled inwardly from a compressor of a gas turbine engine, the method comprising:
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i) providing circumferentially spaced-apart radial passageways extending from an axial passage extending through the compressor in a central area thereof to an outer peripheral rim of a compressor hub; ii) bleeding compressed air from a gas path of the compressor through said radial passageways and directing said compressed air to said axial passage when said compressor rotor assembly is rotating; and iii) directing at least some of the compressed air bled from said axial passage, via a central axially-extending passage of the compressor rotor assembly, to a turbine section of said gas turbine engine to cool turbine components in said turbine section. - View Dependent Claims (16, 17, 18, 19)
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Specification