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INTERCOOLED COOLING AIR

  • US 20190323789A1
  • Filed: 07/03/2019
  • Published: 10/24/2019
  • Est. Priority Date: 02/12/2015
  • Status: Abandoned Application
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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