General Electric Company

Steven James Murphy

Darrell Glenn Senile

Michael Ray Tuertscher

Bryce Loring Heitman

Brian Gregg Feie

Daniel Gene Dunn

Reza Sarrafi-Nour

Henry Charles McGuigan

Douglas Glenn Decesare

Matthew Harper Hockemeyer

Greg Scott Phelps

A composite component for a gas turbine engine is provided, along with its methods of formation. The composite component includes: an additively printed inner portion defining at least one flowpath feature, and a ceramic matrix composite (CMC) outer portion formed on the additively printed inner portion such that the CMC outer portion substantially surrounds the additively printed inner portion. The additively printed inner portion includes SiC; and the CMC outer portion includes a fiber reinforced ceramic matrix (e.g., including SiC) and defines at least one cooling cavity fluidly coupled to the at least one flowpath feature of the additively printed inner portion.

Composite component having an additively printed inner portion

An airfoil assembly for a gas turbine engine and a method of transferring load from the ceramic matrix composite (CMC) airfoil assembly to a metallic vane assembly support member are provided. The airfoil assembly includes a forward end and an aft end with respect to an axial direction of the gas turbine engine. The airfoil assembly includes a radially outer end component, a radially inner end component, and a hollow airfoil body extending therebetween. The radially outer end component including a radially outwardly-facing end surface having a non-compression load-bearing feature extending radially outwardly and formed integrally with the outer end component, the load-bearing feature configured to mate with a complementary feature formed in a radially inner surface of a first airfoil assembly support structure and selectively positioned orthogonally to a force imparted into the airfoil assembly.

Method and system for interfacing a ceramic matrix composite component to a metallic component

Methods for positioning neighboring nozzles of a gas turbine engine are provided. A method includes assembling a first nozzle assembly. The first nozzle assembly includes a first nozzle and a first nozzle support structure. The method further includes assembling a second nozzle assembly. The second nozzle assembly includes a second nozzle and a second nozzle support structure. The method further includes adjusting the first nozzle assembly and the second nozzle assembly such that an engineering dimension between the first nozzle and the second nozzle is within a predetermined engineering tolerance, and joining the first nozzle support structure and the second nozzle support structure together.

Methods for positioning neighboring nozzles of a gas turbine engine

Growing community of inventors

Cincinnati, OH, United States of America

Steven James Murphy