RADIAL COOLING SYSTEM FOR GAS TURBINE ENGINE COMPRESSORS
First Claim
1. A gas turbine engine, comprising:
- a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades;
a first bore cavity between the first rotor and the second rotor;
a first fluid passageway configured to provide cooled air to the first bore cavity; and
a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.
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Accused Products
Abstract
A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.
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Citations
20 Claims
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1. A gas turbine engine, comprising:
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a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades; a first bore cavity between the first rotor and the second rotor; a first fluid passageway configured to provide cooled air to the first bore cavity; and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A compressor for a gas turbine engine, comprising:
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a first rotor supporting a first plurality of circumferentially spaced rotor blades, a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades and a third rotor disposed axially downstream of the second rotor and supporting a third plurality of circumferentially spaced rotor blades; a first bore cavity between the first rotor and the second rotor and a second bore cavity between the second rotor and the third rotor; a fluid passageway configured to provide cooled air to the first bore cavity and the second bore cavity; a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity; and a second anti-vortex component positioned proximate the second bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the second bore cavity. - View Dependent Claims (16, 17, 18, 19, 20)
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Specification