General Electric Company

Thomas Allen Wells

Mark Eugene Noe

David Edward Bulman

Christopher Charles Glynn

Harold Ray Hansel

Toby George Darkins, Jr

John David Bibler

Nitin Bhate

Craig Patrick Burns

Krista Anne Mitchell

Joseph John Charneski

Ian Francis Prentice

John Ellington Greene

Jr Toby George Darkins

A ceramic matrix composite nozzle assembly. The ceramic matrix composite nozzle assembly may include a ceramic matrix composite vane, a number of metallic components positioned about the ceramic matrix composite vane, and a number of metallic seals positioned between the ceramic matrix composite vane and one or more of the metallic components.

Ceramic matrix composite vane seals

A collar seal is configured for a turbine nozzle vane. The seal includes a retainer having a circumferential airfoil contour conforming with the airfoil contour of the vane. A flexible leaf is surrounded by the retainer and fixedly joined thereto. A woven sheath encases the leaf and is fixedly joined to the retainer. In an exemplary embodiment, the collar seal surrounds one end of a ceramic turbine vane mounted in a metal supporting band.

Turbine vane collar seal

An assembly for mounting an igniter in a gas turbine engine combustor between an outer casing and an outer liner, wherein a longitudinal centerline axis extends through the gas turbine engine. The igniter mounting assembly includes a first spring member encircling a portion of said igniter and being positioned between a surface adjacent the outer casing and an outer surface of the outer liner, a first ring member connected to a first end of the first spring member adjacent the outer surface of the outer liner, and a second ring member connected to a second end of the first spring member adjacent the surface adjacent the outer casing. Accordingly, the igniter is able to maintain substantial alignment with respect to an opening in the outer liner while moving radially and/or axially with respect to the outer liner as the outer casing experiences thermal growth greater than the outer liner.

Mounting assembly for igniter in a gas turbine engine combustor having a ceramic matrix composite liner

A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings. In this way, the cowl aft portion and the dome portion are fixedly connected together between the bushing and the nut so that the bushings are able to slide radially through the openings in the liner forward end as the cowl and the dome experience thermal growth greater than the liner.

Mounting assembly for the forward end of a ceramic matrix composite liner in a gas turbine engine combustor

A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

Mounting assembly for the aft end of a ceramic matrix composite liner in a gas turbine engine combustor

A coupling for joining a pair of conduits, one of the conduits having a flared end and the other of the conduits having a circumferential flange with a surface conforming generally for mating with the flared end of the one of the conduits. The coupling comprises a first annular ring positioned about the one of the conduits and having an inner diameter less than an outer diameter of the flared end and a radially inner surface adapted for engaging an outer surface of the flared end. A second annular ring is positioned about the other of the conduits and has an inner diameter less than an outer diameter of the circumferential flange and has a surface adapted for engaging a surface of the flange. A split ring circumscribes the first and second rings and has a radially inner, generally V-shaped groove for simultaneously overlapping both the first and second rings. The split ring has first and second circumferentially spaced ends joined by a bolt for drawing the split ring tightly about the first and second rings so that the first and second rings are urged toward each other by opposing sides of the V-shaped groove for coupling the pair of conduits.

Growing community of inventors

West Chester, OH, United States of America

Thomas Allen Wells