Rtx Corporation

Raytheon Technologies Corporation

United Technologies Corporation

Daniel P Preuss

Dominic J Mongillo, Jr

Nicholas J Madonna

Kristopher K Anderson

Mary Colby

Brandon W Spangler

Andrew Joseph Lazur

Howard J Liles

Timothy J Jennings

Jeffrey Michael Jacques

Lane Mikal Thornton

Brendan M Lenz

Jeremy B Fredette

Justin M Aniello

Robin Michael Patrick Prenter

Melissa Shallcross

Christina A Ryan

Dominic J Mongillo Jr

A tooling fixture suitable for use in infiltrating a fibrous preform with a reactant gas includes an outer surface and opposing inner surface defining a thickness therebetween, and a plurality of holes extending through the thickness. Each hole of the plurality of holes includes an inlet at the outer surface, the inlet configured to receive a flow of the reactant gas, an outlet at the inner surface, a transition point between the inlet and the outlet, and an angled segment extending from the transition point to the outlet. Each hole of the plurality of holes has a first diameter at the inlet and a second diameter at the outlet, and the second diameter is greater than the first diameter.

Chemical vapor infiltration tooling hole modification for optimizing infiltration in ceramic matrix composites

A tooling fixture suitable for use in infiltrating a fibrous preform with a flow of reactant gas includes at least one wall. The at least one wall includes an outer surface and opposing inner surface defining a thickness therebetween, and a plurality of holes extending through the thickness. Each hole of the plurality of holes includes an inlet at the outer surface, an outlet at the inner surface, a transition point between the inlet and the outlet, and a first corner defined by the outer surface and the inlet. An angle of the first corner is less than 90 degrees, each hole of the plurality of holes has a first diameter at the inlet and a second diameter at the outlet, and the second diameter is less than the first diameter.

Chemical vapor infiltration tooling for optimizing infiltration in ceramic matrix composites

Vane assemblies for gas turbine engines are described. The vane assemblies include a platform having an interior platform surface, a forward rail, and an aft rail defining a plenum. An airfoil extends radially inward from the platform on a side opposite the forward and aft rails and includes a leading edge cavity that is open at the platform. A platform feed structure is arranged on the platform about the leading edge cavity and in the plenum and defines a fluid path through the forward rail and into the leading edge cavity. A cover plate is arranged on a top surface of the platform feed structure and configured to fluidly separate the plenum of the platform from the leading edge cavity and define a turning plenum. The cover plate defines a turning contour surface that is shaped to turn an airflow from an axial flow direction to a radial flow direction.

Vane forward rail for gas turbine engine assembly

An impingement apparatus, containing a chamber defined by sides forming the chamber, a plurality of impingement holes located on a side of the chamber, which are able to act as a plurality of flow passages for a coolant fluid to pass from the chamber through the plurality of impingement holes to impinge of a surface to be cooled, one or more metering holes located on one or more sides of the chamber other than on the side on which the impingement holes are located, which are able to act as one or more flow passages for the coolant fluid to pass from an exterior coolant fluid source into the chamber, wherein the pressure created by the coolant fluid inside the chamber is lower than the pressure of the exterior coolant fluid source before entering the chamber through the one or more metering holes.

Self-metering impingement plate

A hollow airfoil body includes a baffle that is arranged in the airfoil body that extends in a radial direction and provides a fluid flow direction. The baffle has multiple holes that include first and second holes that are configured to conduct the cooling airflow in a chordwise direction toward the trailing edge of the airfoil body. The airfoil has a first standoff that extends from the airfoil body to support the baffle. The first axial standoff has a first length that defines an axial passage including the multiple holes. The airfoil includes a second standoff that has a second length less than the first length. The second standoff is arranged radially between the first and second holes. The first hole is smaller than the second hole. The second hole is downstream from the first hole relative to the fluid flow direction.

Hybrid supply configuration for axially flowing high internal mach number baffles

Vane assemblies for gas turbine engines are described. The vane assemblies include a platform having an interior platform surface, a forward rail, and an aft rail, wherein the interior platform surface, the forward rail, and the aft rail define a plenum, an airfoil extending radially inward from the platform on a side opposite the forward and aft rails, the airfoil having a leading edge cavity and a baffle installed within the leading edge cavity, and platform feed structure arranged on the platform in the plenum and defining a fluid path through the forward rail and into the baffle of the leading edge cavity.

Baffles for installation within airfoils include a baffle body defining a feed cavity and extending between inner and outer diameter ends. A forward standoff shelf is formed along an exterior surface of the baffle and defined by a depression, bend, or channel in a material of the baffle body extending between the inner and outer diameter ends. The forward standoff shelf is configured to engage with a forward rail of the airfoil body, and an aft standoff shelf is formed along an exterior surface of the baffle body and configured to engage with an aft rail of the airfoil body. A surface of the baffle body between the forward standoff shelf and the aft standoff shelf defines a side channel surface extending in a radial direction along the baffle body between the outer diameter end and the inner diameter end.

Components for gas turbine engines

A gas turbine engine includes a compressor section rotatable about an axis, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section includes a vane assembly including a radially outer platform with respect to the axis. A first airfoil extend from the radially outer platform to a radially inner platform. A rail extends radially inward from the inner platform, and a connected passage includes an airfoil passage within the first airfoil. A platform passage is located within the inner platform, and a rail passage is located within the rail. The airfoil passage, the platform passage, and the rail passage are fluidly connected.

Vane core assemblies and methods

A gas turbine engine includes a compressor section that provides first and second compressor stages that are configured to respectively provide first and second cooling fluids. The first compressor stage has a higher pressure than the second compressor stage. The gas turbine engine further includes a component that has platform with an internal cooling passage fed by first and second inlets that respectively receive fluid from the first and second cooling sources. The second inlet is downstream from the first inlet.

Platform serpentine re-supply

Airfoil assemblies for gas turbine engines include an airfoil body and a leading edge baffle installed within a leading edge cavity of the airfoil body. The airfoil body includes a plurality of radially extending rails configured to engage with the baffle and define radially extending channels therebetween. First and second forward radially extending rails are segmented in the radial direction and a showerhead radial channel is defined along the leading edge. Pressure and suction side radial flow channels are defined between an interior surface of the airfoil body, an exterior surface of the baffle, and radially extending rails. An aft channel is defined between an interior surface of the airfoil body along pressure and suction side walls, an interior rib, exterior surfaces of the baffle, and the radially extending rails.

Components for gas turbine engines are described. The components include an airfoil having a leading edge cavity with a baffle portion and a leading edge portion. A baffle is installed within the baffle portion and includes a first metering flow aperture. A first support element retention feature is located within the leading edge cavity. A first axial extending rib extends between an aft end of the cavity and a forward end proximate the first support element retention feature and is formed on an interior surface of the airfoil. A first axial extending flow channel extends along the first axial extending rib between an exterior surface of the baffle and an interior surface of the airfoil and the first metering flow aperture is located proximate the aft end of the first axial extending flow channel to generate a forward flowing cooling flow.

Vane assemblies are described. The vane assemblies include a platform, an airfoil extending from the platform, a forward rail extending from the platform and arranged along a forward side of the platform, and an aft rail extending from the platform and arranged along an aft side of the platform. At least one support beam is provided extending in a forward-aft direction between the forward rail and the aft rail and separated from the platform by a first distance. The at least one support beam has a thickness in a radial direction of 40% or less of a total radial extent from the platform to an outer diameter edge of at least one of the forward rail and the aft rail and the at least one support beam has a thickness in a circumferential direction of 30% or less of a total circumferential extent of vane assembly.

Rail support beams

An airfoil for a gas turbine engine includes axial flow and radial flow cooling circuits defined within an airfoil body. A baffle disposed in spaced relation to an inner surface of the airfoil has a plurality of impingement cooling holes configured to direct a cooling fluid at an inner surface of the airfoil body and an axial extent from the leading edge defined by an aft wall, with the axial extent being substantially constant between the inner and outer end walls and defined by a plane perpendicular to an engine axis. A first radially-extending rib is angled with respect to the baffle to define a first passage between the first rib and the baffle that tapers in cross-sectional area between the inner end wall and the outer end wall, becoming larger in cross-sectional area in a direction of cooling fluid flow through the first passage.

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Newington, CT, United States of America

Daniel P Preuss