Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.