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Patent Searching and Data


Title:
COOLING HOLE MACHINING METHOD FOR GAS TURBINE BLADE
Document Type and Number:
Japanese Patent JPH09136260
Kind Code:
A
Abstract:

To save labor as against a conventional way in which ceramic coating is applied after perforation is carried out and to prevent generation of a crack, which may be caused when perforation is carried out in a ceramic coating layer, a bond coating layer, and a blade base member at a stroke by means of laser beam machining, in the blade base member in the vicinity of a cooling hole.

After a ceramic coating layer 3 in the place in which a cooling hole is arranged is removed by means of shot blasting, electric discharge machining is applied to an exposed bond coating layer 2 in this place and a blade base member 1, and then, a through hole serving as a cooling hole is formed. In this way, a crack, which was conventionally caused in the blade member 1 around the cooling hole when laser beam machining was carried out, is prevented, so that a sound and precise cooling hole can be provided with ease.


Inventors:
SHIGE TAKASHI
BEPPU SEIJI
Application Number:
JP29666595A
Publication Date:
May 27, 1997
Filing Date:
November 15, 1995
Export Citation:
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Assignee:
MITSUBISHI HEAVY IND LTD
International Classes:
B24C1/00; F01D5/18; F02C7/00; (IPC1-7): B24C1/00; F01D5/18; F02C7/00
Attorney, Agent or Firm:
Akasaka Saka (1 person outside)