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Title: Turbomachine blade assembly

Patent ·
OSTI ID:1330701

Embodiments of the present disclosure include a system comprising a turbomachine blade assembly having a blade portion, a shank portion, and a mounting portion, wherein the blade portion, the shank portion, and the mounting portion comprise a first plurality of plies extending from a tip of the airfoil to a base of the dovetail.

Research Organization:
General Electric Co., Schenectady, NY (United States)
Sponsoring Organization:
USDOE
DOE Contract Number:
FC26-05NT42643
Assignee:
General Electric Company (Schenectady, NY)
Patent Number(s):
9,482,108
Application Number:
13/856,303
OSTI ID:
1330701
Resource Relation:
Patent File Date: 2013 Apr 03
Country of Publication:
United States
Language:
English

References (15)

Turbine rotor with pin mounted ceramic turbine blades patent April 1978
Composite ceramic gas turbine blade patent August 1981
Platform assembly for attaching rotor blades to a rotor disk patent June 1993
Composite fan blade trailing edge reinforcement patent July 1998
Cooled turbine spar shell blade construction patent July 2006
Bond coat for silicon-containing substrate for EBC and processes for preparing same patent October 2008
Composite blading member and method for making patent March 2009
Composite turbine blade patent June 2011
Abrasive thermal coating patent May 2012
Modular turbine airfoil and platform assembly with independent root teeth patent July 2013
Method for producing a turbomachine blade made from a composite material patent December 2013
Ceramic matrix composite blade having integral platform structures and methods of fabrication patent May 2014
Composite airfoil assembly patent March 2015
Composite material turbomachine engine blade or vane, compressor stator segment or turbine nozzle segment incorporating such vanes and method for manufacturing same patent June 2015
Method for Producing a Turbomachine Blade Made from a Composite Material patent-application March 2012

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