Turbine bucket for use in gas turbine engines and methods for fabricating the same
Abstract
A turbine bucket for use with a turbine engine. The turbine bucket includes an airfoil that extends between a root end and a tip end. The airfoil includes an outer wall that defines a cavity that extends from the root end to the tip end. The outer wall includes a first ceramic matrix composite (CMC) substrate that extends a first distance from the root end to the tip end. An inner wall is positioned within the cavity. The inner wall includes a second CMC substrate that extends a second distance from the root end towards the tip end that is different than the first distance.
- Inventors:
- Issue Date:
- Research Org.:
- NETL (National Energy Technology Laboratory, Pittsburgh, PA, and Morgantown, WV (United States))
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1133683
- Patent Number(s):
- 8,740,571
- Application Number:
- 13/042,034
- Assignee:
- 8,740,571
- DOE Contract Number:
- FC26-05NT42643
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Garcia-Crespo, Andres. Turbine bucket for use in gas turbine engines and methods for fabricating the same. United States: N. p., 2014.
Web.
Garcia-Crespo, Andres. Turbine bucket for use in gas turbine engines and methods for fabricating the same. United States.
Garcia-Crespo, Andres. Tue .
"Turbine bucket for use in gas turbine engines and methods for fabricating the same". United States. https://www.osti.gov/servlets/purl/1133683.
@article{osti_1133683,
title = {Turbine bucket for use in gas turbine engines and methods for fabricating the same},
author = {Garcia-Crespo, Andres},
abstractNote = {A turbine bucket for use with a turbine engine. The turbine bucket includes an airfoil that extends between a root end and a tip end. The airfoil includes an outer wall that defines a cavity that extends from the root end to the tip end. The outer wall includes a first ceramic matrix composite (CMC) substrate that extends a first distance from the root end to the tip end. An inner wall is positioned within the cavity. The inner wall includes a second CMC substrate that extends a second distance from the root end towards the tip end that is different than the first distance.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2014},
month = {6}
}
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Works referenced in this record:
Turbine blade or turbine vane made of a ceramic foam joined to a metallic nonfoam, and preparation thereof
patent, November 2003
- Grylls, Richard; Austin, Curtiss; Linko, Peter
- US Patent Document 6,648,596
High temperature abradable coatings
patent-application, July 2005
- Lau, Yuk-Chiu; Ghasripoor, Farshad; Fusaro, JR., Robert Anthony
- US Patent Application 11/033813; 20050164027
Works referencing / citing this record:
Cold spray method for producing gas turbine blade tip
patent-application, October 2007
- Allen, David B.
- US Patent Application 11/208296; 20070248750
Turbine blade with ceramic tip
patent-application, December 2007
- Downs, James P.
- US Patent Application 11/206471, 20070292273
Fan blade made of a textile composite material
patent-application, August 2008
- Schreiber, Karl
- US Patent Application 11/907958; 20080187441
Method and system for manufacturing a blade
patent-application, February 2010
- Kray, Nicholas; Davis, Tod; McAfee, Christopher
- US Patent Application 12/183805; 20100028594