General Electric Company

Brian Keith

Paul Hadley Vitt

Ching-Pang Lee

Kevin Samuel Klasing

Ronald Eugene McRae, Jr

Jonathan Philip Clarke

Robert Alan Frederick

Thomas William Vandeputte

Andrew Charles Powis

Edward Eugene Gibler

Jonathan Jordan Peterman

Daniel Endecott Osgood

Aspi Rustom Wadia

Brian Chandler Barr

David Alan Frey

Prem Venugopal

Alexander Martin Sener

Gregory John Kajfasz

Jamil Darnell Grant

Jeffrey Donald Clements

Gregory Terrence Garay

Jan Christopher Schilling

Kirk Douglas Gallier

Steven Robert Brassfield

Xi Yang

Douglas Gerard Konitzer

Tingfan Pang

Meredith Elissa Dubelman

Brian David Przeslawski

Chander Prakash

David Glenn Cherry

Leslie Eugene Leeke, Jr

Brian Alan Norton

Scott Michael Carson

Michael Scott Cole

Stephen Mark Molter

Harjit Singh Hura

Jonathan Ong

Joseph Machnaim

William Charles Herman

Matthew Brian Surprenant

Vidhu Shekhar Pandey

Andrew Edward Obermeyer

Nicole Barba

Peter Frank Martinello

A turbine engine includes a compressor section, a combustion section, and a turbine section, and an airfoil with an outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line. A first thickness is defined between the pressure side and the suction side at a first location along the mean camber line.

Turbine engine airfoil

A variable guide vane assembly is provided for a turbine defining a core air flowpath. The variable guide vane assembly includes an airfoil band defining a flowpath surface and a cavity. The variable guide vane assembly further includes an airfoil including a first end extending at least partially into the cavity of the airfoil band and an opposite second end, the airfoil extending generally along an axis between the first end and the second end and being moveable generally about the axis relative to the airfoil band. The variable guide vane assembly further includes a sealing element operable to form a seal between the first end of the airfoil and the airfoil band.

Variable guide vane sealing

A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.

Airfoil assembly with flow surface

Integrated core-shell investment casting molds that provide tongue or groove structures corresponding, respectively, to groove or tongue structures in the surface of the turbine blade or stator vane, including in locations that are otherwise inaccessible provide a pathway to restrict cooling flow between turbine blades to the flowpath.

Integrated casting core-shell structure for making cast component with novel cooling hole architecture

An apparatus and method for controlling a flow of fluid through a nozzle assembly including a set of nozzles. The nozzles can have a set of airfoils defining a throat between the airfoils. One or more exhaust holes can be provided in the airfoils downstream of the throat. A fluid supply line can be fluidly coupled to the exhaust holes for selectively supplying a flow of fluid through the exhaust holes.

Turbine engine with variable effective throat

A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 30% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils.

Gas turbine engine transition duct and turbine center frame

An apparatus and method of cooling a tip of an airfoil for a gas turbine engine, includes a rib circumscribing the tip to define a tip plenum. A tip baffle partially divides the tip plenum, being spaced from the rib by a baffle slot. The rib includes a tip slot in fluid communication with the baffle slot to provide a flow of cooling fluid along the tip of the airfoil for exhausting out the tip slot.

Gas turbine engine airfoil

A transition duct for use in a turbine engine is provided. The transition duct includes a radially inner wall and a radially outer wall positioned about the radially inner wall defining a flow passage therebetween. The radially outer wall extends and is contoured from an upstream end to a downstream end of the transition duct. As such, the slope of the radially outer wall increases from the upstream end to a predetermined axial location and decreases from the predetermined axial location to the downstream end.

Transition duct for use in a turbine engine and method of assembly

A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. Each platform has a scalloped flow surface including a purge trough commencing tangentially in a blend area of the platform. The purge trough extending axially toward the suction side of the airfoil, aft of the leading edge, to channel a purge flow.

Scalloped surface turbine stage with purge trough

A turbine stage includes a row of airfoils joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure and suction sides and extends in chord between opposite leading and trailing edges. At least some of the platforms have a scalloped flow surface including a bulge adjoining the pressure side and a bowl adjoining the suction side, aft of the leading edge, of the respective airfoils. The bulge is configured having a maximum height located within its respective flow passage, and wherein the bulge decreases in height in a forward and aft direction and decreases in height laterally toward the pressure side of the airfoil and toward the bowl adjoining the suction side of a next adjacent airfoil.

Scalloped surface turbine stage

A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.

Flared tip turbine blade

A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.

Tip ramp turbine blade

A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.

Cascade tip baffle airfoil

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Cincinnati, OH, United States of America

Brian Keith