Dual interstage cooled engine
AssigneeGeneral Electric Company
InventorsChing-Pang Lee, Thomas Ory Moniz, Robert Joseph Orlando
Life of this patent
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Abstract
A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. A first interstage bleed circuit is joined in flow communication between a first preultimate stage of the compressor and hollow blades in the turbine to provide thereto pressurized primary air. A second interstage bleed circuit is joined in flow communication between a second preultimate stage of the compressor and the turbine blades to provide thereto pressurized secondary air at a lower pressure than the primary air.
Claims25
A gas turbine engine comprising:
- a fan, compressor, combustor, high pressure (HP) turbine and low pressure (LP) turbine in serial flow communication;
- said compressor including rows of compressor blades for pressurizing air sequentially in corresponding stages;
- said HP turbine including a single stage row of hollow rotor blades mounted in corresponding dovetail slots in the perimeter of a supporting rotor disk;
- said LP turbine including a row of hollow first stage LP vanes following said HP blades;
- a first interstage bleed circuit joined in flow communication from a bleed inlet extending radially inwardly between adjacent rows of said compressor blades in a first preultimate stage of said compressor to said HP blades inboard of said combustor;
- and
- a second interstage bleed circuit joined in flow communication between a second preultimate stage of said compressor and said HP blades outboard of said combustor and through said LP vanes.
A gas turbine engine comprising:
- a multistage compressor disposed in serial flow communication with a combustor and high pressure (HP) turbine;
- said turbine including a row of first stage turbine rotor blades extending radially outwardly from a supporting rotor disk;
- each of said blades including a forward cooling channel feeding leading edge cooling holes, and an aft cooling channel feeding trailing edge cooling holes;
- a first interstage bleed circuit joined in flow communication from a bleed inlet extending radially inwardly between adjacent rows of compressor blades in a first preultimate stage of said compressor to said blade forward channels to provide thereto pressurized primary air at a first pressure;
- and
- a second interstage bleed circuit joined in flow communication between a second preultimate stage of said compressor and said blade aft channels to provide thereto pressurized secondary air at a second pressure lower than said first pressure.
A method of cooling first stage blades following in turn a combustor and compressor in a gas turbine engine, comprising:
- bleeding primary air from a bleed inlet extending radially inwardly between adjacent rows of compressor blades in a first preultimate stage of said compressor to a forward cooling channel in said blades for discharge from leading edge cooling holes therein;
- and
- bleeding secondary air between a different second preultimate stage of said compressor and an aft cooling channel in said blades for discharge from trailing edge cooling holes therein.
Dependencies are inferred from the claim text.