General Electric Company

Other

Robert Frederick Bergholz

Aaron Ezekiel Smith

Daniel Lee Durstock

Weston Nolan Dooley

Matthew Lee Krumanaker

Steven Robert Brassfield

Robert David Briggs

Kevin Robert Feldmann

Ronald Scott Bunker

Robert Francis Manning

Zachary Daniel Webster

Curtis Walton Stover

Jason Randolph Allen

Shawn Michael Pearson

Stephen Mark Molter

Douglas Ray Smith

Frederick Alan Buck

Fernando Reiter

An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.

Engine component assembly

A gas turbine engine wall is provided. The wall includes an inner surface and an opposing outer surface having at least one film cooling hole defined therein. The at least one film cooling hole includes an inclined inlet bore that extends from the inner surface and a pair of channels that diverge laterally from an outlet end of the inclined inlet bore. The pair of channels have a substantially constant width and are separated by a ridge to form a boomerang cross-sectional shape.

Gas turbine engine wall

An engine component for a gas turbine engine includes a film-cooled recess comprising a contoured portion defining a step. A hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow are fluidly coupled by a passage through the engine component. The passage further comprises an inlet in the cooling surface and an outlet in the step. The inlet, passage and outlet are oriented such that the cooling fluid flowing through the passage and exiting the outlet diffuses within the contoured portion prevents premature mixing out with the hot fluid flow.

Engine component for a gas turbine engine

An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

Turbine blade

An engine comprises an airfoil having at least one internal cooling circuit extending radially from the longitudinal axis of the engine. The cooling circuit is defined by at least one rib extending across an interior of the airfoil and at least one internal wall defining an internal passage. The internal wall further defines one or more near wall cooling passages. A thermal stress reduction structure is provided between the rib and the internal wall, providing efficient cooling at a junction between the rib and the internal wall.

A turbine engine comprises an airfoil having one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.

A turbine component includes a component wall with inner and outer surfaces wherein a diffuser hole passes through the component wall between the inner surface and the outer surface. The diffuser hole has a hole axis and includes: a metering section extending from an inlet at the inner surface to a junction plane between the inner and outer surfaces; and a diffuser section extending from the junction plane to an outlet at the outer surface, and increasing in flow area from the junction plane to the outlet, the diffuser section having an upstream portion defining a first area ratio and a downstream portion defining a second area ratio different from the first area ratio.

Turbine engine component with diffuser holes

An engine component includes a hot surface in thermal communication with a hot combustion gas flow, and a cooling surface, opposite the hot surface, along which a cooling fluid flows. At least one vortex generator is provided on the cooling surface, and can induce a vortex in the cooling fluid in response to contact with the flowing cooling fluid.

Engine component

A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in the pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge. Each cooling hole includes in downstream serial cooling flow relationship, a curved inlet, a constant area and constant width metering section, and a spanwise diverging section leading into the trailing edge cooling slot, and a spanwise height substantially greater than a hole width through the cooling hole. A pressure sidewall surface of the pressure sidewall may be planar through the metering and diverging sections. The width may be constant through the metering and diverging sections. A raised floor may include a flat up ramp in the diverging section, a flat down ramp in the slot.

Turbine airfoil trailing edge cooling slots

A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to trailing edge. Each cooling hole includes an asymmetric flow cross section through one or more asymmetric intermediate sections leading into slot. Flow cross section is asymmetric with respect to a mid-plane extending axially and spanwise through intermediate sections. Different trailing edge cooling holes may include different asymmetric flow cross sections. Lands may extend between the cooling slots. A raised floor may extend away from at least one of pressure or suction sidewalls at least partially through one or more asymmetric intermediate sections and optionally at least partially through cooling slot. Raised floor may include up and down ramps and a flat transition section between ramps.

Asymmetrically shaped trailing edge cooling holes

A turbine airfoil includes pressure and suction sidewalls extending along a span from a base to a tip. Spanwise spaced apart trailing edge cooling holes in the pressure sidewall end at corresponding spanwise spaced apart trailing edge cooling slots extending chordally substantially to the trailing edge. Each cooling hole includes a plug extending downstream through at least a portion of a spanwise diverging section leading into the slot. The plug may be spanwise centered in the hole and may include a plug dome rising up from a plug base extending along a suction sidewall surface of the suction sidewall. The cooling hole may further include an inlet leading to a metering section with a constant area and constant width flow cross section upstream of spanwise diverging section. Lands may be disposed between the trailing edge cooling slots forming slot floors between lands.

A cooling system for a gas turbine engine including a compressor, a combustor and a high-pressure turbine, coupled together in serial flow arrangement. The cooling system includes a storage tank, a working fluid stored within the storage tank, and a manifold coupled to the channel that supplies cooling air to the high pressure turbine. The working fluid is discharged from the manifold into the turbine cooling air supply channel, thereby reducing the temperature of the compressed cooling airflow channeled to the high pressure turbine.

Growing community of inventors

Loveland, OH, United States of America

Robert Frederick Bergholz