INTERCOOLED COOLING AIR
First Claim
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1. A gas turbine engine comprising;
- a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations;
a turbine section having a high pressure turbine;
a tap tapping air from at least one of said more upstream locations in said compressor section, passing said tapped air through a heat exchanger and then to a cooling compressor, said cooling compressor compressing air downstream of said heat exchanger, and delivering air into said high pressure turbine; and
said turbine section further having a fan drive turbine, said fan drive turbine driving a main fan through a main fan gear reduction, said main fan delivering air into a bypass duct as bypass air and into said main compressor section, a bypass ratio being defined as a volume of air delivered into said bypass duct divided by a volume of air delivered into said main compressor section, and said bypass ratio being greater than or equal to 10.0, a gear ratio of said main fan gear reduction being greater than or equal to 2.3, a low fan pressure ratio across said main fan being less than or equal to 1.45, and said main fan having an actual fan tip speed in feet/second that is less than or equal to 1150 feet/second.
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Abstract
A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.
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Citations
20 Claims
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1. A gas turbine engine comprising;
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a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations; a turbine section having a high pressure turbine; a tap tapping air from at least one of said more upstream locations in said compressor section, passing said tapped air through a heat exchanger and then to a cooling compressor, said cooling compressor compressing air downstream of said heat exchanger, and delivering air into said high pressure turbine; and said turbine section further having a fan drive turbine, said fan drive turbine driving a main fan through a main fan gear reduction, said main fan delivering air into a bypass duct as bypass air and into said main compressor section, a bypass ratio being defined as a volume of air delivered into said bypass duct divided by a volume of air delivered into said main compressor section, and said bypass ratio being greater than or equal to 10.0, a gear ratio of said main fan gear reduction being greater than or equal to 2.3, a low fan pressure ratio across said main fan being less than or equal to 1.45, and said main fan having an actual fan tip speed in feet/second that is less than or equal to 1150 feet/second. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14)
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15. A gas turbine engine comprising;
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a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations; a turbine section having a high pressure turbine; a tap tapping air from at least one of said more upstream locations in said compressor section, passing said tapped air through a heat exchanger and then to a cooling compressor, said cooling compressor compressing air downstream of said heat exchanger, and delivering air into said high pressure turbine; said turbine section further having a fan drive turbine, said fan drive turbine driving a main fan through a main fan gear reduction, said main fan delivering air into a bypass duct as bypass air and into said main compressor section, a bypass ratio being defined as a volume of air delivered into said bypass duct divided by a volume of air delivered into said main compressor section, and said bypass ratio being greater than or equal to 10.0, a gear ratio of said main fan gear reduction being greater than or equal to 2.3, a low fan pressure ratio across said main fan being less than or equal to 1.45, and said main fan having an actual fan tip speed in feet/second that is less than or equal to 1150 feet/second; wherein said heat exchanger positioned within said bypass duct to be cooled by bypass air; wherein said turbine section driving a tower shaft, said tower shaft further driving an impeller of said cooling compressor; and wherein said tower shaft also driving an accessory gearbox. - View Dependent Claims (16, 17, 18, 19, 20)
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Specification