Turbine cooling cycle

Claim 2

An air flow delivery system for providing a combustion fluid and for providing a cooling fluid to cool components of a gas turbine engine having a compressor section, said air flow delivery system comprising: a first fluid flow path interconnecting the compressor section with the combustor section, said compressor section including a plurality of blades having a first blade portion causing a fluid flow within the first fluid flow path when the compressor section is in operation and at least one of said plurality of blades includes a two-story blade configuration and wherein said two-story blade configuration includes a root portion, a platform portion projecting radial therefrom, the first blade portion extending radial from the platform portion, an outer tip defined on the first blade portion, a ring segment being attached to the outer tip and the second blade portion extending radially from the ring segment; and a second fluid flow path interconnecting the first fluid flow path with the components of the gas turbine engine to be cooled, said second fluid flow path including a heat exchanger interposed the first fluid flow path and the components to be cooled, said second fluid flow path having a flow of cooling air therein being formed by the operation of a second blade portion being formed on the plurality of blades.

Claim 3

The air flow delivery system of claim 1 wherein said first fluid flow path includes a passage in which the first blade portion is positioned.

Claim 4

The air flow delivery system of claim 2 wherein said second fluid flow path includes a gallery in which the second blade portion is positioned.

Claim 5

The air flow delivery system of claim 3 wherein said passage is separated from said gallery.

Claim 6

An air flow delivery system for providing a combustion fluid and for providing a cooling fluid to cool components of a gas turbine engine having a compressor section, said air flow delivery system comprising: a first fluid flow path interconnecting the compressor section with the combustor section, said compressor section including a plurality of blades having a first blade portion causing a fluid flow within the first fluid flow path when the compressor section is in operation; and a second fluid flow path interconnecting the first fluid flow path with the components of the gas turbine engine to be cooled, said second fluid flow path including a heat exchanger interposed the first fluid flow path and the components to be cooled, said heat exchanger is externally mounted from the gas turbine engine, said second fluid flow path having a flow of cooling air therein being formed by the operation of a second blade portion being formed on the plurality of blades.

Claim 7

An air flow delivery system for providing a combustion fluid and for providing a cooling fluid to cool components of a gas turbine engine having a compressor section, said air flow delivery system comprising: a first fluid flow path interconnecting the compressor section with the combustor section, said compressor section including a plurality of blades having a first blade portion causing a fluid flow within the first fluid flow path when the compressor section is in operation; and a second fluid flow path interconnecting the first fluid flow path with the components of the gas turbine engine to be cooled, said second fluid flow path including a heat exchanger interposed the first fluid flow path and the components to be cooled, said heat exchanger is externally mounted from the gas turbine engine, said second fluid flow path having a flow of cooling air therein being formed by the operation of a second blade portion being formed on the plurality of blades.

Claim 8

The air flow delivery system of claim 5 wherein said heat exchanger is of the tube fin configuration.

Claim 9

The air flow delivery system of claim 1 wherein said heat exchanger is internally mounted within the gas turbine engine.

Claim 10

The air flow delivery system of claim 1 wherein said heat exchanger includes a closed system containing an inert or nonflammable fluid.

Claim 11

An air flow delivery system for use with a gas turbine engine, said gas turbine engine including a compressor section having a plurality of stages each having a disc in which a plurality of blades are attached thereto, and a combustor section and a turbine section positioned in operative relationship therewith, said air flow delivery system comprising: a portion of said plurality of blades defining a two-stage configuration including a root portion, a platform portion projecting radial therefrom, the first blade portion extending radial from the platform portion, and outer tip defined on the first blade portion, said first blade portion being spaced from a second blade portion by a ring segment; a first fluid flow path including a passage in which the first blade portion is positioned, and said first fluid flow path being in fluid flow communication with the turbine section; a second fluid flow path including a gallery in which the second blade portion is positioned, said gallery being in fluid communication with the first fluid flow path; a fluid flow being created within the first fluid flow path by the first blade portion during operation of the compressor section, said flow being generally used to provide a flow of fluid to the combustor section; a flow of cooling fluid being created within the second fluid flow path by the second blade portion during operation of the compressor section, said flow being generally used to provide a flow of cooling fluid to cool components of the gas turbine engine.

Claim 12

An air flow delivery system for use with a gas turbine engine, said gas turbine engine including a compressor section having a plurality of stages each having a disc in which a plurality of blades are attached thereto, and a combustor section and a turbine section positioned in operative relationship therewith, said air flow delivery system comprising: a portion of said plurality of blades defining a two-stage configuration including a root portion, a platform portion projecting radial therefrom, the first blade portion extending radial from the platform portion, and outer tip defined on the first blade portion, said first blade portion being spaced from a second blade portion by a ring segment; a first fluid flow path including a passage in which the first blade portion is positioned, and said first fluid flow path being in fluid flow communication with the turbine section; a second fluid flow path including a gallery in which the second blade portion is positioned, said gallery being in fluid communication with the first fluid flow path; a fluid flow being created within the first fluid flow path by the first blade portion during operation of the compressor section, said flow being generally used to provide a flow of fluid to the combustor section; a flow of cooling fluid being created within the second fluid flow path by the second blade portion during operation of the compressor section, said flow being generally used to provide a flow of cooling fluid to cool components of the gas turbine engine.

Claim 13

The air flow delivery system of claim 9 wherein said fluid for creating the flow of cooling fluid is drawn from the fluid flowing within the first fluid flow path.

Claim 14

The air flow delivery system of claim 9 wherein said second fluid flow path includes a heat exchanger operative positioned within the flow of cooling fluid.

Claim 15

The air flow delivery system of claim 11 wherein said heat exchanger includes a heat exchanging medium, having a gaseous state.

Claim 16

The air flow delivery system of claim 11 wherein said heat exchanger includes a heat exchanging medium, having a liquid state.

Claim 17

The air flow delivery system of claim 13 wherein said heat exchanging medium is a combustible liquid being use within the combustor section of the gas turbine engine.

Claim 18

The air flow delivery system of claim 13 wherein said heat exchanging medium is a liquid being used within the combustor section for reducing emissions emitted from the gas turbine engine.

Claim 19

The air flow delivery system of claim 15 wherein said liquid is water.

Claim 20

The air flow delivery system of claim 11 wherein said heat exchanger is of the tube to fin configuration.

Claim 21

The air flow delivery system of claim 11 wherein said heat exchanger is of the primary surface configuration.

Claim 22

The air flow delivery system of claim 18 wherein said primary surface configuration of the heat exchanger uses air as the cooling medium.

Claim 23

The air flow delivery system of claim 11 wherein said heat exchanger includes a closed system containing an inert or nonflammable fluid.

Claim 24

The air flow delivery system of claim 8 wherein said heat exchanger has a heat exchanging medium having a liquid state.

Claim 25

The air flow delivery system of claim 21 wherein said liquid is water.