United Technologies Corporation

Raytheon Technologies Corporation

John McBrien

Thomas N Slavens

Timothy J Jennings

Brandon W Spangler

Nicholas M LoRicco

Sasha M Moore

Clifford J Musto

San Quach

Lea Kennard Castle

JinQuan Xu

Carey J Clum

Christopher Whitfield

Matthew A Devore

Bret M Teller

David A Niezelski

Nicholas M Lo Ricco

Jinquan Xu

Nicholas M Loricco

Thomas N Stevens

Sacha M Moore

Airfoils for gas turbine engines are described. The airfoils include an airfoil body extending between a platform and a tip, the airfoil body having a leading edge, a trailing edge, a pressure side, and a suction side, a serpentine cavity formed within the airfoil body and having an up-pass serpentine cavity, a down-pass serpentine cavity, and a trailing edge cavity, and a dead-end tip flag cavity extending in a direction between the leading edge and the trailing edge, the dead-end tip flag cavity arrange between the serpentine cavity and the tip, wherein the dead-end tip flag cavity ends at a dead-end wall located at a position between the leading edge and the trailing edge of the airfoil body.

Airfoil having dead-end tip flag cavity

A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. The wall has a wall thickness. A protrusion is arranged on the wall that extends a height beyond the wall thickness and provides a portion of the interior flow path surface. A film cooling hole that has an inlet is provided on the protrusion and extends to an exit on the exterior surface.

Gas turbine engine component with film cooling hole

A gas turbine engine component includes a body with a wall surrounding an interior cavity. The wall has opposed interior and exterior surfaces. The interior surface has a plurality of coolant inlets and the exterior surface has a coolant outlet defined therein. A coolant conduit extends between the coolant inlets and the coolant outlet and is configured and adapted to induce secondary flow vortices in coolant traversing the coolant conduit and in an adherent coolant film over a portion of the exterior surface of component body.

Cooling for gas turbine engine components

A gas turbine engine component is described. The component includes a component wall having an internal surface that is adjacent a flow of coolant and an external surface that is adjacent a flow of gas. The component wall includes a cooling hole that has an inlet defined by the internal surface and an outlet defined by the external surface. The cooling holes also has a metering location having the smallest cross-section area of the cooling hole, an internal diffuser positioned between the inlet and the metering location, an accumulation diverter portion of the internal diffuser and an accumulator portion of the internal diffuser.

Film hole with in-wall accumulator

A wall of a gas turbine engine is provided. The wall may comprise an external surface adjacent a gas path and an internal surface adjacent an internal flow path. A film hole may have an inlet at the internal surface and an outlet at the external surface. A flow accumulator adjacent the inlet may protrude from the internal surface. A method of making an engine component is also provided and comprises the step of forming a component wall comprising an accumulator on an internal surface and a film hole defined by the component wall. The film hole may include an opening adjacent the accumulator and defined by the internal surface.

Film hole with protruding flow accumulator

A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.

Gas turbine engine component with film cooling hole with accumulator

An intermediate component with an internal passageway includes a solid metallic additively manufactured component with an internal passageway in a near finished shape. The component has voids greater than 0 percent but less than approximately 15 percent by volume and up to 15 percent additional material by volume in the near finished shape compared to a desired finished configuration. Also included are a ceramic core disposed within the internal passageway of the component and an outer ceramic shell mold encasing an entirety of the component, such that an entire external surface of the component is covered by the outer ceramic shell mold.

Intermediate additively manufactured component

A method of forming a metal single crystal turbine component with internal passageways includes forming a polycrystalline turbine blade with internal passageways by additive manufacturing and filling the passageways with a core ceramic slurry. The ceramic slurry is then treated to harden the core and the turbine component is encased in a ceramic shell which is treated to form a ceramic mold. The turbine component in the mold is then melted and directionally solidified in the form of a single crystal. The outer shell and inner ceramic core are then removed to form a finished single crystal turbine component with internal passageways.

Method for forming single crystal parts using additive manufacturing and remelt

A gas turbine engine component includes a structure having an exterior surface. A cooling hole extends from a cooling passage to the exterior surface to provide an exit area on the exterior surface that is substantially circular in shape. A gas turbine engine includes a compressor section and a turbine section. A combustor is provided between the compressor and turbine sections. A component in at least one of the compressor and turbine sections has an exterior surface. A film cooling hole extends from a cooling passage to the exterior surface to provide an exit area that is substantially circular in shape. A method of machining a film cooling hole includes providing a component having an internal cooling passage and an exterior surface, machining a film cooling hole from the exterior surface to the internal cooling passage to provide a substantially circular exit area on the exterior surface.

Gas turbine engine cooling hole with circular exit geometry

One embodiment includes a method to regenerate a component (). The method includes additively manufacturing a component () to have voids greater than 0 percent but less than approximately 15 percent in a near finished shape. The component () is encased in a shell mold (). The shell mold () is cured. The encased component () is placed in a furnace and the component () is melted. The component () is solidified in the shell mold (). The shell mold () is removed from the solidified component ().

Regenerating an additively manufactured component

One embodiment includes a method to regenerate a component. The method includes additively manufacturing the component with at least a portion of the component in a near finished shape. The component is encased in a shell mold, the shell mold is cured, the encased component is placed in a furnace and the component is melted, the component is solidified in the shell mold, and the shell mold is removed from the solidified component.

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South Glastonbury, CT, United States of America

John McBrien