Title:
ガスタービンエンジン翼形部の耐用寿命を延ばすための方法及び装置
Document Type and Number:
Japanese Patent JP4208504
Kind Code:
B2
Abstract:
A gas turbine engine includes a blade (40) including a leading edge (48), a trailing edge (50), a first sidewall (44) extending in radial span between a blade root (52) and blade tip (54), and a second sidewall (46) connected to the first sidewall at the leading edge and at the trailing edge. The first and second sidewalls each include an outer surface (60) and an inner surface (72). A cooling cavity (70) is defined by the first sidewall inner surface and the second sidewall inner surface. At least a portion of the cooling cavity is coated with an oxidation resistant environmental coating that has a thickness (110) less than 0.0015 inches.
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Inventors:
John Peter Hayward
Roger Dale Ustsman
Timothy Lane Norris
Richard Clay Howbert
Paul John Fink
Roger Dale Ustsman
Timothy Lane Norris
Richard Clay Howbert
Paul John Fink
Application Number:
JP2002196609A
Publication Date:
January 14, 2009
Filing Date:
July 05, 2002
Export Citation:
Assignee:
GENERAL ELECTRIC COMPANY
International Classes:
F01D5/28; C23C10/06; C23C30/00; F01D5/18; F01D25/00; F02C7/00
Domestic Patent References:
| JP2001172775A |
Foreign References:
| WO1999003599A1 | ||||
| US5215785 | ||||
| US6180170 | ||||
| EP1077273A1 |
Attorney, Agent or Firm:
Kenichi Matsumoto
Hirokazu Ogura
Nobukazu Ito
Hirokazu Ogura
Nobukazu Ito