Rtx Corporation

Raytheon Technologies Corporation

United Technologies Corporation

Jonas S Banhos

James T Roach

Russell Kim

Raymond C Surace

Tracy A Propheter-Hinckley

Michael Parkin

Cheng Gao

Andre Herman Troughton

William Meyst

Anthony Prainito

Ravon Venters

Kathryn S Read

Olivier H Sudre

Jesse Ian Berube

Scott D Hjelm

Jesus S Lopez

Joo Sub Rhee

Anthony J Prainito

Thiago B Vieira

Ravi Mandya Kumar

Nicholas Andrew Kesler

William Oldach

Scott David Hjelm

A combined gas turbine engine vane and blade outer air seal assembly includes a vane having an airfoil extending from the leading edge to a trailing edge, and has an outer platform. The outer platform has a cooling channel that extends into the airfoil to receive cooling air. The outer platform extends to an integral blade outer air seal to be positioned radially outwardly of a turbine blade in a gas turbine engine. At least a portion of the vane and the blade outer air seal are formed of ceramic matrix composite materials. A gas turbine engine is also disclosed.

Gas turbine engine vane outer diameter platform integrated with blade outer air seal

An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side, a flange that extends from the non-gaspath side, and a gaspath side from which the airfoil section extends. The flange is comprised of a sandwich composite that includes first and second ceramic matrix composite (CMC) skins that each have at least one 2-D ceramic fiber ply, and a cellular core disposed between the first and second CMC skins.

Airfoil with sandwich composite flange

An airfoil includes a platform and an airfoil section that are formed of a ceramic matrix composite that includes core fiber plies, skin fiber plies, platform fiber plies, and a cooling passage that extends through selected ones of the plies to provide a cooling circuit through the airfoil section and into the platform.

CMC airfoil with cooling passage formed in fiber plies

A gas turbine engine stator vane combination includes a stator vane body having an airfoil with a leading edge, a trailing edge, a suction side and a pressure side, and having at least one internal cooling channel. The stator vane body is formed of ceramic matrix composite materials. A spar is received within the at least one cooling air channel and formed of a metal. The spar has an outer peripheral surface spaced from an inner peripheral surface of the cooling air channel to define a cooling air path, with the cooling air path having a varying cross-sectional area through the cooling air channel. A gas turbine engine is also disclosed.

Gas turbine engine vane and spar combination with variable air flow path

A method includes forming an airfoil, where the airfoil includes an airfoil wall that has a span between first and second radial ends and defines leading and trailing edges, pressure and suction sides each join the leading and trailing edges, and an internal cavity, the internal cavity is divided into at least first and second sub-cavities that extend over the span, and the first sub-cavity defines a venturi tube. The forming includes i) fabricating a fiber preform of the airfoil around a plurality of mandrels, wherein the mandrel in the first sub-cavity is radially split, and ii) densifying the fiber preform with a ceramic matrix. The airfoil may include an internal cavity that is divided into at least first and second sub-cavities extending over the span, where the first sub-cavity defines a venturi tube.

Airfoil with venturi tube

A combustor includes a combustion chamber and a liner that bounds at least a portion of the combustion chamber. The liner includes a first side facing the combustion chamber and a second side facing away from the combustion chamber. The liner is formed of a lay-up of ceramic matrix composite (CMC) plies that have a first CMC ply on the first side, a second CMC ply on the second side, and intermediate CMC plies between the first and second CMC plies. At least one of the intermediate CMC plies has a pattern of voids that define cooling channels in the combustor panel. The cooling channels are bound on lateral channel sides by the at least one of the intermediate CMC plies.

Combustor liner with pattern of voids in CMC fiber ply for cooling channels

A gas turbine engine component includes an airfoil body extending between a leading edge and a trailing edge and having a suction wall and a pressure wall. An outer surface of the airfoil body is formed by an outer coat defining around the pressure and suction sides, a leading edge and a trailing edge. An internal cross-rib is formed within a cavity in the airfoil body. The internal cross-rib extends to be secured to the outer coat adjacent the leading edge and the trailing edge, and extending across the internal cavity to form a junction such that the cross-rib is x-shaped. The outer coat and the cross-rib are formed of ceramic matrix composites. A gas turbine engine is also disclosed.

Gas turbine engine component having an airfoil with internal cross-ribs

A flange stiffener support for a duct in a gas turbine engine includes a circumferential flange segment that has a plurality of flange fastener openings. An axial body segment extends from a radially inner side of the circumferential segment and has at least one body fastener opening. The axial body segment extends at least partially along a circumferential distance of the circumferential flange segment.

Flange and assembly for gas turbine engine case

An airfoil includes an airfoil wall that circumscribes a main cavity and defines radially inner and outer ends, leading and trailing edges, and pressure and suction sides. The airfoil wall includes a lay-up of ceramic matrix composite (CMC) plies that span the radially inner and outer ends and have an inner-most CMC ply bounding at least a portion of the main cavity, an exterior skin CMC ply, and intermediate CMC plies between the inner-most CMC ply and the exterior skin CMC ply. At least one of the intermediate CMC plies has cutout voids that define cooling channels in the airfoil wall. The cooling channels are bound on lateral sides by the at least one of the intermediate CMC plies, bound on an inner side by a first adjacent one of the CMC plies, and bound on an outer side by a second, different adjacent one of the CMC plies.

Airfoil with CMC ply cutouts for cooling channels

A ceramic matrix composite airfoil includes a high-pressure surface and a low-pressure surface connected at a leading edge and a trailing edge. The high-pressure surface and the low-pressure surface extend from a first end to a second end. A leading edge cooling passage includes an inlet portion, a midspan portion and an outlet portion. A cross-sectional flow area of the midspan portion is less than a cross-sectional flow area of either the inlet portion or the outlet portion.

Airfoil leading edge venturi cooling passage

A seal arc segment includes a wall that defines radially inner and outer sides, forward and aft ends, and first and second circumferential sides. The wall includes a CMC ply lay-up of a radially inner-most CMC ply on the inner side, a radially outer-most CMC ply on the radially outer side, and radially intermediate CMC plies therebetween. At least one of the radially intermediate CMC plies has cutout voids that define cooling channels in the wall. The cooling channels are bound on lateral channel sides by the at least one of the radially intermediate CMC plies, bound on a radially inner channel side by a first adjacent one of the CMC plies, and bound on a radially outer channel side by a second, different adjacent one of the CMC plies. The radially outer-most CMC ply includes at least one inlet hole connected to the cooling channels for providing cooling air.

Seal arc segment with CMC ply cutouts for cooling channels

An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side and a gaspath side from which the airfoil section extends. The platform is comprised of a sandwich composite that has first and second ceramic matrix composite (CMC) skins that each include at least one 2-D ceramic fiber ply. The first and second CMC skins are disposed, respectively, on the gaspath side and the non-gaspath side, and there is a cellular core disposed radially between the first and second CMC skins.

Airfoil with sandwich composite

An airfoil includes an airfoil wall that has a span between first and second radial ends and that defines leading and trailing edges, pressure and suction sides each joining the leading and trailing edges, and an internal cavity. The internal cavity is divided into at least first and second sub-cavities extending over the span. The first sub-cavity defines a venturi tube.

A method of forming a ceramic matrix composite airfoil includes forming a fibrous ceramic preform by laying up a plurality of plies to form a hollow core cavity, overwrapping the plurality of plies of the core cavity with a first overwrap layer, weaving together a tows of first free portion and tows of a second free portion of the first overwrap layer to form a cross brace, overwrapping the plurality of plies of the core cavity and the first overwrap layer with a second overwrap layer, and consolidating the first free portion and the second free portion of the first overwrap layer and a third free portion and a fourth free portion of the second overwrap layer to form a trailing edge.

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Rocky Hill, CT, United States of America

Jonas S Banhos