초록 ▼

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 channel

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.

대표청구항 ▼

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 1. A gas turbine engine comprising:a multistage axial compressor including rows of compressor blades for pressurizing air;an ann

Accordingly, what is desired to be secured by Letters Patent of the United States is the invention as defined and differentiated in the following claims in which we claim: 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; andan 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.