COOLING ARRANGEMENT FOR PLATFORM REGION OF TURBINE ROTOR BLADE

Title:

COOLING ARRANGEMENT FOR PLATFORM REGION OF TURBINE ROTOR BLADE

Document Type and Number:

Japanese Patent JP2014047786

Kind Code:

A

Abstract:

To provide durable, long-lasting rotor blade platforms that perform well and are cost-effective to manufacture.

Provided is a platform cooling arrangement in a turbine rotor blade having a platform 110 at an interface between an airfoil 102 and a wing root. The platform may include a pressure side slashface and a suction side slashface. The platform cooling arrangement may include a cooling channel 136 formed within the interior of the platform, the cooling channel extending from a first end toward one of the pressure side slashface and the suction side slashface. At a second end, the cooling channel may include a pocket 144. The pocket may include an abrupt increase in cross-sectional flow area just before the cooling channel reaches the slashface.

Inventors:

ZHANG XIUZHANG JAMES
KESTER CHRISTOPHER WILLIAM
SAMPAYO CAMILO ANDRES
BENSON ADEBUKOLA OLUWASEUN

Application Number:

JP2013175115A

Publication Date:

March 17, 2014

Filing Date:

August 27, 2013

Export Citation:

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Assignee:

GEN ELECTRIC

International Classes:

F01D5/18

Domestic Patent References:

JP2012077745A

2012-04-19

Foreign References:

US20110020115A1	2011-01-27
GB1605335A	1991-12-18
US5382135A	1995-01-17

Attorney, Agent or Firm:

Arakawa Satoshi
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka

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