Compressor core inner diameter cooling
AssigneeUnited Technologies Corporation
InventorsGabriel L. Suciu, Brian D. Merry, Jesse M. Chandler, William K. Ackermann, Matthew R. Feulner, Om P. Sharma
Life of this patent
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Abstract
A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
Claims18
A compressor section for use in a gas turbine engine comprising:
- a compressor rotor having a hub and a plurality of blades extending radially outwardly from said hub and an outer housing surrounding an outer periphery of said blades;
- an annular duct upstream of the compressor rotor configured to deliver a core engine flow to the plurality of blades;
- and
- a tap for tapping air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet through a radially inner wall of the annular duct, the outlet at a second location which is radially inward of said first location, radially outward of said hub, and within the core engine flow, the outlet positioned to provide cooling air adjacent to said hub and passing along a radially outer surface of said hub.
A gas turbine engine comprising:
- a compressor section;
- a combustor;
- a turbine section;
- said compressor section including a compressor rotor having a hub and a plurality of blades extending radially outwardly from said hub and an outer housing surrounding an outer periphery of said blades;
- an annular duct upstream of the compressor rotor configured to deliver a core engine flow to the plurality of blades;
- and
- a tap for tapping air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet through a radially inner wall of the annular duct, the outlet at a second location which is radially inward of said first location, radially outward of said hub, and within the core engine flow, the outlet positioned to provide cooling air adjacent to said hub and passing along a radially outer surface of said hub.
Dependencies are inferred from the claim text.