General Electric Company

Ge Infrastructure Technology, LLC

David Wayne Weber

Gregory Thomas Foster

Brendon James Leary

Michelle Jessica Iduate

Aaron Ezekiel Smith

Nicholas William Rathay

Gustavo Adolfo Ledezma

Gregory Terrence Garay

Victor John Morgan

Neelesh Nandkumar Sarawate

Thomas Earl Dyson

Joseph Anthony Weber

Dustin Michael Earnhardt

Benjamin Paul Lacy

Jacob Charles Perry, Ii

Lana Maria Osusky

Christopher Lee Golden

Gary Michael Itzel

David Edward Schick

Sandip Dutta

Christopher Donald Porter

Neil Devin Ristau

Zachary James Taylor

Robert Peter Hanet

Elisabeth Kraus Black

Michelle Jessica Rogers

Srikanth Chandrudu Kottilingam

Zachary John Snider

Robert Frank Hoskin

Robert Walter Coign

Omprakash Samudrala

Satoshi Atsuchi

Bryan David Lewis

Kevin Thomas McGovern

Stephen William Tesh

Mehmet Suleyman Ciray

Brandon Lee Cox

Joseph Antony Weber

Jacob Charles Perry Ii

Kevin Mcgovern

Jospeh Anthony Weber

Ii Jacob Charles Perry

An airfoil includes a leading edge, a trailing edge, a pressure side wall, and a suction side wall. The pressure side wall and the suction side wall each extend between the leading edge and the trailing edge. A camber axis is defined halfway between the pressure side wall and the suction side wall. A cooling circuit is defined in the airfoil. The cooling circuit includes a trailing edge cooling circuit. The trailing edge cooling circuit has a pressure side channel that is disposed at least partially on a first side of the camber axis and a suction side channel that is disposed at least partially on a second side of the camber axis. The pressure side channel and the suction side channel each converge towards the trailing edge as the pressure side channel and the suction side channel extend towards the trailing edge.

Trailing edge cooling circuit

An airfoil includes a body, a cooling passage, a first cooling cavity, a second cooling cavity, a cooling conduit, and a connecting conduit. The body defines an interior and includes a tip rail with an exterior surface extending between a first surface, a second surface, and a third surface. The cooling passage is formed within the interior. The first cooling cavity and the second cooling cavity are spaced from each other within the tip rail. The cooling conduit fluidly couples the cooling passage with the first cooling cavity. The connecting conduit fluidly couples the first cooling cavity to the second cooling cavity.

Blade with tip rail cooling

A blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting the pressure side outer wall and the suction side outer wall and partitioning the radially extending chamber into a leading edge passage within the leading edge of the airfoil and a central passage adjacent to the leading edge passage. One or both camber line ribs connect to a corresponding pressure side outer wall and suction side outer wall at a point aft of the leading edge transverse rib causing the central passage to extend towards one or both of the pressure side outer wall and the suction side outer wall, resulting in a flared center cavity aft of the leading edge.

Flared central cavity aft of airfoil leading edge

An apparatus and method for cooling a blade tip for a turbine engine can include an blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall enclosing an interior for the blade at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the blade to cool the tip of the blade.

Blade with tip rail, cooling

Turbine shrouds including internal cooling passages are disclosed. The shrouds may include a unitary body including a support portion, an intermediate portion formed integral with and extending from the support portion, and a seal portion formed integral with the intermediate portion, opposite the support portion. The unitary body may also include two opposing slash faces extending between the support portion and the seal portion, a HGP seal slot formed on each of the two opposing slash faces, and at least one plenum and cooling passage extending through the support portion, intermediate portion, and/or the seal portion. The unitary body may also include an exhaust channel and slash face exhaust holes formed in each of the two opposing slash faces. The exhaust channel may be in fluid communication with the cooling passage(s), and the slash face exhaust holes may be in fluid communication with the exhaust channel.

Unitary body turbine shrouds including internal cooling passages

An apparatus and method for cooling an airfoil tip for a turbine engine can include a blade, such as a cooled turbine blade, having a tip rail extending beyond a tip wall () enclosing an interior for the airfoil at the tip. A plurality of film-holes can be provided in the tip rail. A flow of cooling fluid can be provided through the film-holes from the interior of the airfoil to cool the tip of the airfoil.

Airfoil with tip rail cooling

Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge; and a tip shroud connected with a second end of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the tip shroud including a tip shroud fillet connecting the airfoil and the tip shroud and having a non-uniform thickness across an axial length of the airfoil.

Turbine bucket having tip shroud fillet, tip shroud cross-drilled apertures and profile

A cooling assembly includes a cooling chamber disposed inside of a turbine assembly. The cooling chamber directs cooling air inside an airfoil of the turbine assembly. The cooling assembly includes a metered channel fluidly coupled with the cooling chamber. The metered channel directs at least some of the cooling air out of the cooling chamber outside of a rail surface of the airfoil. The metered channel is elongated along and encompasses an axis. The metered channel has an interior surface with a distance between opposing first portions of the interior surface. The distance between the opposing first portions decreases at increasing distances along the axis from the cooling chamber toward the rail surface.

Cooling assembly for a turbine assembly

One aspect of the disclosure provides for a turbine airfoil. The turbine airfoil may include a trailing edge having: a set of cooling channels having a first cooling channel fluidly connected to a second cooling channel; a first section having a first pin bank cooling arrangement, the first section fluidly connected to the first cooling channel; a second section having a second pin bank cooling arrangement, the second section fluidly connected to the second cooling channel and being radially inward of the first section; and a pressure side panel having a third pin bank cooling arrangement, the pressure side panel fluidly connected to the first cooling channel.

Turbine airfoil with trailing edge cooling circuit

A turbine blade includes an airfoil defined by a pressure side outer wall and a suction side outer wall connecting along leading and trailing edges and form a radially extending chamber for receiving a coolant flow. A rib configuration may include: a leading edge transverse rib connecting to the pressure side outer wall and the suction side outer wall and partitioning a leading edge passage from the radially extending chamber. The rib configuration may also include a first center transverse rib connecting to the pressure side outer wall and the suction side outer wall and partitioning an intermediate passage from the radially extending chamber directly aft of the leading edge passage. The intermediate passage is defined by the pressure side outer wall, the suction side outer wall, the leading edge transverse rib and the first center transverse rib, and thus spans airfoil between its outer walls.

Intermediate central passage spanning outer walls aft of airfoil leading edge passage

An edge coupon for an airfoil is provided. The coupon includes: a coupon body including: a coolant feed; an outward leg extending toward an edge of the coupon and fluidly coupled to the coolant feed; a return leg extending away from the edge of the coupon and radially offset from the outward leg along a radial axis of the coupon; a turn for fluidly coupling the outward leg and the return leg; a collection passage fluidly coupled to the return leg; and a coupling region configured to mate with an airfoil body of the airfoil.

Edge coupon including cooling circuit for airfoil

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Simpsonville, SC, United States of America

David Wayne Weber