Interstage cooled turbine engine
First Claim
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1. A gas turbine engine comprising:
- a multistage axial compressor including rows of compressor blades for pressurizing air;
an annular combustor disposed in flow communication with said compressor for mixing fuel with said pressurized air to generate combustion gases;
a high pressure (HP) turbine including a row of first stage HP turbine blades having dovetails mounted in corresponding dovetail slots in the perimeter of a supporting HP rotor disk joined by a shaft to said compressor blades;
said HP disk including a web extending inwardly from said perimeter with a forward face terminating in a wider hub, and a forward seal plate extending radially along said forward face to define an annular manifold in flow communication with said dovetail slots; and
an interstage cooling circuit joined in flow communication from a bleed inlet extending radially inwardly between adjacent rows of said compressor blades in an intermediate stage of said compressor to said manifold for channeling interstage bleed cooling air thereto.
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Abstract
A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.
59 Citations
29 Claims
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1. A gas turbine engine comprising:
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a multistage axial compressor including rows of compressor blades for pressurizing air; an annular combustor disposed in flow communication with said compressor for mixing fuel with said pressurized air to generate combustion gases; a high pressure (HP) turbine including a row of first stage HP turbine blades having dovetails mounted in corresponding dovetail slots in the perimeter of a supporting HP rotor disk joined by a shaft to said compressor blades; said HP disk including a web extending inwardly from said perimeter with a forward face terminating in a wider hub, and a forward seal plate extending radially along said forward face to define an annular manifold in flow communication with said dovetail slots; and an interstage cooling circuit joined in flow communication from a bleed inlet extending radially inwardly between adjacent rows of said compressor blades in an intermediate stage of said compressor to said manifold for channeling interstage bleed cooling air thereto. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A gas turbine engine comprising:
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a multistage compressor including rows of compressor blades for pressurizing air; a combustor disposed in flow communication with said compressor for mixing fuel with said pressurized air to generate combustion gases; a high pressure (HP) turbine including a row of first stage HP turbine blades mounted to the perimeter of an HP rotor disk joined by a shaft to said compressor blades, and disposed in flow communication with said combustor for extracting energy from said gases to power said compressor; and an interstage cooling circuit joined in flow communication from a bleed inlet extending radially inwardly between adjacent rows of said compressor blades in an intermediate stage of said compressor to a forward face of said HP disk between said shaft and said HP blades for channeling interstage bleed cooling air thereto. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20, 21, 22, 23, 24, 25)
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26. A method of cooling a high pressure (HP) turbine in gas turbine engine having a multistage compressor providing pressurized air to a combustor for generating hot combustion gases from which energy is extracted in said turbine, comprising:
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bleeding interstage pressurized air radially inwardly from between adjacent blade rows in said compressor; channeling said interstage bleed air to a forward face of a first stage HP disk in said turbine for cooling thereof; and channeling said interstage air radially outwardly over said forward face into dovetail slots in the perimeter of said disk. - View Dependent Claims (27, 28, 29)
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Specification