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Dual interstage cooled engine

  • US 7,926,289 B2
  • Filed: 11/10/2006
  • Issued: 04/19/2011
  • Est. Priority Date: 11/10/2006
  • Status: Expired due to Fees
First Claim
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1. A gas turbine engine comprising:

  • a fan, compressor, combustor, high pressure (HP) turbine and low pressure (LP) turbine in serial flow communication;

    said compressor including rows of compressor blades for pressurizing air sequentially in corresponding stages;

    said HP turbine including a single stage row of hollow rotor blades mounted in corresponding dovetail slots in the perimeter of a supporting rotor disk;

    said LP turbine including a row of hollow first stage LP vanes following said HP blades;

    a first interstage bleed circuit joined in flow communication from a bleed inlet extending radially inwardly between adjacent rows of said compressor blades in a first preultimate stage of said compressor to said HP blades inboard of said combustor; and

    a second interstage bleed circuit joined in flow communication between a second preultimate stage of said compressor and said HP blades outboard of said combustor and through said LP vanes.

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