초록 ▼

Air flow delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by directing a portion of a compressed air formed by the compressor section and located in a first flu

Air flow delivery systems for gas turbine engines are used to increase component life and increase power and efficiencies. The present system increases the component life and increases efficiencies by directing a portion of a compressed air formed by the compressor section and located in a first fluid flow path to a second fluid flow path including a heat exchanger positioned operatively within the second flow path. The second fluid flow path results in a flow of cooled cooling air to be directed to the components of the gas turbine engine to be cooled. Thus, the components of the gas turbine engine are more efficiently cooled with a smaller quantity of air drawn from the compressor section generated air than if compressor generated air was used for cooling components of the gas turbine engine. Furthermore, more compressor generated air remains for combustion within the combustor section of the gas turbine engine.

대표청구항 ▼

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,

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.