General Electric Company

Emily Rosette Clark

Jeffrey Douglas Rambo

Thomas Kupiszewski

William Stewart

Ronald Scott Bunker

Kirk Douglas Gallier

Todd Garrett Wetzel

Thomas Earl Dyson

Brian Gene Brzek

James Fredric Wiedenhoefer

Weston Nolan Dooley

Jonathan Michael Rausch

Julienne LaChance

Daniel Robinson Getsinger

James Richard Winka

Flow paths and boundary layer restart features are provided. For example, a flow path comprises a flow path wall defining an inner flow path surface and an asymmetric notch defined in the flow path wall. The asymmetric notch comprises a first surface and a second surface and is asymmetric about a first line extending through an intersection of the first and second surfaces. Further, a flow boundary layer restart feature comprises a first surface extending inward with respect to a flow path surface of a flow path and a second surface extending inward with respect to the flow path surface. The second surface is asymmetric with respect to the first surface such that the first and second surfaces define an asymmetric notch. Additionally, a flow path wall may comprise an asymmetric notch that includes a flow expansion angle and a flow contraction angle that are unequal.

Asymmetric flow path topology

An apparatus for cooling an engine component such as a turbine engine airfoil, including a wall bounding an interior extending axially between a leading edge and a trailing edge and radially between a root and a tip. A cooling circuit it located within the interior of the airfoil can include a flow enhancer permitting a volume of fluid, such as air, to pass around the flow enhancer.

Engine component with flow enhancer

An engine component assembly includes an engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface in fluid communication with a cooling fluid flow. Multiple, non-linear channels are provided on the cooling surface of the engine component. At least a portion of the cooling fluid flow is orthogonal to an extension axis of the channels.

Engine component assembly

An apparatus and method for cooling an engine component such as an airfoil can include an outer wall separating a cooling fluid flow from a hot flow. A cooling circuit can be provided in the engine component including a cooling passage having at least one pin within the cooling passage with a chevron shape and a non-uniform configuration.

Engine component with non-uniform chevron pins

An apparatus and method for cooling an engine component, such as an airfoil, for a turbine engine including an outer wall separating a cooling fluid flow from a hot fluid flow. A cooling circuit including a cooling passage having opposing sidewalls can be provided in the engine component. At least one turbulator can be provided between the opposing sidewalls, and can include a conduit having an inlet and an outlet passing through the at least one turbulator.

Engine component with hollow turbulators

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Cincinnati, OH, United States of America

Emily Rosette Clark