Composite turbine bucket assembly
Abstract
A composite turbine blade assembly includes a ceramic blade including an airfoil portion, a shank portion and an attachment portion; and a transition assembly adapted to attach the ceramic blade to a turbine disk or rotor, the transition assembly including first and second transition components clamped together, trapping said ceramic airfoil therebetween. Interior surfaces of the first and second transition portions are formed to mate with the shank portion and the attachment portion of the ceramic blade, and exterior surfaces of said first and second transition components are formed to include an attachment feature enabling the transition assembly to be attached to the turbine rotor or disk.
- Inventors:
- Publication Date:
- Research Org.:
- General Electric Co., Schenectady, NY (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1132514
- Patent Number(s):
- 8,727,730
- Application Number:
- 12/754,689
- Assignee:
- General Electric Company (Schenectady, NY)
- DOE Contract Number:
- FC26-05NT42643
- Resource Type:
- Patent
- Resource Relation:
- Patent File Date: 2010 Apr 06
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Liotta, Gary Charles, and Garcia-Crespo, Andres. Composite turbine bucket assembly. United States: N. p., 2014.
Web.
Liotta, Gary Charles, & Garcia-Crespo, Andres. Composite turbine bucket assembly. United States.
Liotta, Gary Charles, and Garcia-Crespo, Andres. 2014.
"Composite turbine bucket assembly". United States. https://www.osti.gov/servlets/purl/1132514.
@article{osti_1132514,
title = {Composite turbine bucket assembly},
author = {Liotta, Gary Charles and Garcia-Crespo, Andres},
abstractNote = {A composite turbine blade assembly includes a ceramic blade including an airfoil portion, a shank portion and an attachment portion; and a transition assembly adapted to attach the ceramic blade to a turbine disk or rotor, the transition assembly including first and second transition components clamped together, trapping said ceramic airfoil therebetween. Interior surfaces of the first and second transition portions are formed to mate with the shank portion and the attachment portion of the ceramic blade, and exterior surfaces of said first and second transition components are formed to include an attachment feature enabling the transition assembly to be attached to the turbine rotor or disk.},
doi = {},
url = {https://www.osti.gov/biblio/1132514},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue May 20 00:00:00 EDT 2014},
month = {Tue May 20 00:00:00 EDT 2014}
}
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Works referencing / citing this record:
Damper for a turbine rotor assembly
patent, May 2016
- Faulder, Leslie John; Tarczy, Jeffrey Eugene
- US Patent Document 9,347,325
Turbomachine blade mounting system
patent, November 2015
- McMurray, Timothy Scott; Farineau, Thomas Joseph
- US Patent Document 9,175,572