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Title:
GAS TURBINE ENGINE COMPONENT EQUIPPED WITH PLATFORM WITH MICRO-CIRCUIT
Document Type and Number:
Japanese Patent JP2005220909
Kind Code:
A
Abstract:

To realize a turbine engine component capable of dramatically reducing a metal temperature gradient in a platform part 20 and of extending a thermal fatigue life.

The gas turbine engine component, such as a high pressure turbine blade, has an aerofoil part 14, the platform 20 and micro-circuits 50, 80 within the platform 20. The micro-circuits 50, 80 cool at least one platform edge adjacent to a positive pressure face 32 of the aerofoil part 14 and the trailing edge of the platform 20. The micro-circuits 50, 80 include a first micro-circuit 50 on an aerofoil negative pressure face 30 and a second micro-circuit 80 on the airfoil positive pressure face 32. The micro-circuits 50, 80 within the platform 20 achieve high thermal convective efficiency, increased film coverage and high cooling effectiveness.


Inventors:
Cunha, Frank
Santeler, Keith
Teller, Bret
Application Number:
JP2005000024660
Publication Date:
August 18, 2005
Filing Date:
February 01, 2005
Export Citation:
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Assignee:
UNITED TECHNOL CORP
International Classes:
F01D5/14; F01D5/18; F02C7/18; (IPC1-7): F02C7/18; F01D5/14
Attorney, Agent or Firm:
橋本 剛
富岡 潔