General Electric Company

Greg Scott Phelps

Michael Ray Tuertscher

Darrell Glenn Senile

Christopher Charles Glynn

Robert Alan Frederick

Michael Alan Stieg

Michael Todd Radwanski

Bryce Loring Heitman

Brian Christopher Towle

Benjamin Scott Huizenga

Brian Gregg Feie

Steven James Murphy

Darell Glenn Senile

Jeff Douglas Johnson

A nozzle assembly is provided which is, in part, formed of a low coefficient of thermal expansion material. The assembly includes a nozzle fairing formed of the low coefficient of thermal expansion material and includes a metallic strut extending radially through the nozzle fairing. Load is transferred from the nozzle fairing to a static structure in either of two ways: first, the strut may receive the load directly and/or second, load may be transferred from the nozzle fairing to at least one of the inner and outer support rings. Further, the nozzle fairing and strut may allow for internal airflow for cooling.

Ceramic matrix composite nozzle mounted with a strut and concepts thereof

A turbine nozzle apparatus includes: a vane extending between inner and outer bands, the interior of the vane being open and communicating with an aperture in the outer band, wherein the vane and the bands are part of a monolithic whole of low-ductility material; a metallic baffle inside the vane, the baffle having upper and lower ends and a peripheral wall including a plurality of impingement holes defining an interior space, closed off by an end wall at the lower end; and a metallic retainer having a body with a shape generally matching the shape of the aperture, the body bearing against the upper end of the impingement baffle and being connected to the outer band by a plurality of mechanical fasteners.

Turbine nozzle with impingement baffle

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

A turbine nozzle includes an arcuate inner band having opposed flowpath and back sides, and an aft flange extending outward from the back side; an arcuate outer band having opposed flowpath and back sides; an airfoil-shaped turbine vane extending between the flowpath sides of the inner and outer bands, wherein the inner and outer bands and the vane comprise a ceramic low-ductility material; and a metallic collar surrounding the aft flange.

Mounting apparatus for low-ductility turbine nozzle

Growing community of inventors

Cincinnati, OH, United States of America

Greg Scott Phelps