Title:
タービン部品の断熱被覆層システム
Document Type and Number:
Japanese Patent JP3863846
Kind Code:
B2
Abstract:
A composite thermal barrier coating system includes a first composite thermal barrier coating over a portion of a substrate, and a second deposited thermal barrier coating over edge portions of the substrate. The first composite coating is relatively thick and preferably includes friable graded insulation comprising an abradable honeycomb metallic structure filled with high thermal expansion ceramic hollow spheres in a phosphate bonded matrix. The second deposited edge coating is relatively thin and preferably comprises an electron beam physical vapor deposited thermal barrier coating comprising ZrO2 and Y2O3. The friable graded insulation may be manufactured to thicknesses in excess of current thermal barrier coating systems, thereby imparting greater thermal protection. Superior erosion resistance and abrasion properties are also achieved. The composite thermal barrier coating system is useful on combustion turbine components such as ring seal segments, vane segment shrouds, transitions and combustors.
Inventors:
Kisia, John, Ewan
Application Number:
JP2002522575A
Publication Date:
December 27, 2006
Filing Date:
August 21, 2001
Export Citation:
Assignee:
SIEMENS WESTINGHOUSE POWER CORPORATION
International Classes:
C23C28/04; C23C4/00; C23C28/00; C23C30/00; F01D5/28; F01D9/02; F01D25/24; F02C7/00
Domestic Patent References:
| JP7090533A | ||||
| JP9511303A | ||||
| JP58067905A | ||||
| JP8327263A |
Attorney, Agent or Firm:
Koichiro Kato