METHOD AND SYSTEM FOR INTERFACING CERAMIC MATRIX COMPOSITE COMPONENT WITH METALLIC COMPONENT

Japanese Patent JP2017025915

A

PROBLEM TO BE SOLVED: To provide a method for interfacing a ceramic matrix composite component with a metallic component in a gas turbine engine.SOLUTION: An airfoil assembly for a gas turbine engine comprises: a forward end and an aft end with respect to an axial direction; and a radially outer end component 216 comprising a radially outwardly facing end surface 302 having a non-compression load-bearing feature extending radially outwardly from the outwardly facing end surface and formed integrally with the outer end component. The feature is configured to mate with a complementary feature formed in a radially inner surface 308 of a first airfoil assembly support structure 214, the feature selectively positioned orthogonally to a force imparted to the airfoil assembly. The airfoil assembly also comprises a radially inner end component 204, and a hollow airfoil body 210 extending therebetween, the airfoil body configured to receive a strut 208 couplable at a first end 206 to the first airfoil assembly support structure.SELECTED DRAWING: Figure 3

BRYCE LORING HEITMAN
SENILE DARRELL G
MICHAEL RAY TUERTSCHER
GREGG SCOTT PHELPS
GREGG FEIE BRIAN
STEVEN JAMES MURPHY

JP2016139002A

February 02, 2017

July 14, 2016

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GENERAL ELECTRIC CO GE

F01D9/02; C04B37/02; F01D25/00; F02C7/00

JP2004076601A	2004-03-11
JP2009041568A	2009-02-26
JP2011508151A	2011-03-10
JP2002021505A	2002-01-23
JP2000320497A	2000-11-21
JP2014088786A	2014-05-15
JPS6166802A	1986-04-05
JP3701680B2	2005-10-05
JP2012519803A	2012-08-30

US20060171812A1	2006-08-03
US20140001285A1	2014-01-02
US20140234118A1	2014-08-21
US6000906A	1999-12-14

Arakawa Satoshi
Hirokazu Ogura
Toshihisa Kurokawa
Takuto Tanaka

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