General Electric Company

Ge Infrastructure Technology, LLC

General Electric Technology Gmbh

Benjamin Paul Lacy

Srikanth Chandrudu Kottilingam

David Edward Schick

Gilbert Otto Kraemer

Willy Steve Ziminsky

Ertan Yilmaz

Balachandar Varatharajan

Sandip Dutta

Thomas Edward Johnson

Baifang Zuo

Gary Michael Itzel

Victor John Morgan

William David York

Christian Xavier Stevenson

Brian Lee Tollison

Brian Peter Arness

Jong Ho Uhm

Carlos Miguel Miranda

Christopher Donald Porter

Ibrahim Sezer

David Wayne Weber

Brian Gene Brzek

John Wesley Harris, Jr

Brad Wilson VanTassel

Ronald Scott Bunker

Patrick Benedict Melton

Zachary John Snider

Andrei Tristan Evulet

Xiuzhang James Zhang

Joseph Anthony Weber

John Joseph Lipinski

Stephen William Tesh

David Kenton Felling

Marc Lionel Benjamin

Bin Wei

Aaron Ezekiel Smith

Gregory Thomas Foster

Stephen Paul Wassynger

Kapil Kumar Singh

Brad Wilson Vantassel

Kassy Moy Hart

Anthony Louis Giglio

James William Vehr

Kathleen Blanche Morey

Dipankar Pal

Ahmed Mostafa ElKady

Lyndsay Marie Kibler

San Jason Nguyen

Lewis Berkley Davis, Jr

Yan Cui

Jon Conrad Schaeffer

Gregory Allen Boardman

Matthew Troy Hafner

Slawomir Rubinsztajn

Paul Stephen DiMascio

Neelesh Nandkumar Sarawate

Richard Martin DiCintio

David Vincent Bucci

Kwanwoo Kim

Andrew Lee Trimmer

Kevin Richard Kirtley

Andres Jose Garcia-Crespo

Jacob John Kittleson

Stanley Frank Simpson

Sarah Lori Crothers

Mehmet Demiroglu

John Ellington Greene

Travis J Packer

Gregory Allan Crum

John Charles Intile

Archie Lee Swanner, Jr

Wilbur Douglas Scheidt

Shiva Kumar Srinivasan

Randall Richard Good

John Joseph Lynch

Ariel Caesar Prepena Jacala

Wenwu Zhang

Thomas James Brunt

David Andrew Helmick

Dustin Michael Earnhardt

Nuo Sheng

Jason Ray Gregg

Matthew Scott Lutz

Mert Enis Berkman

Peter Galen Stevens

Patrick Thomas Walsh

Jane Marie Lipkin

Balachandar Naidu

Brandon Lee Cox

Luis Alfonso Gonzalez

Michael Scott Soden

Raymond Chupp

Brad Wilson Van Tassel

Joseph Antony Weber

Jr John Wesley Harris

Balachander Varatharajan

Varatharajan Balachandar

An airfoil component includes an airfoil body having a pressure side, a suction side, a trailing edge, and an airfoil mount. A collection plenum is defined in the airfoil body and is configured to collect coolant exiting from impingement openings in an impingement member therein. Cooling passages are defined in the airfoil body and in fluid communication with the collection plenum and extend to first film cooling opening(s) in part(s) of the airfoil body. A mount cooling plenum is defined, at least in part, in the airfoil mount and in fluid communication with the collection plenum. Second cooling openings are defined in the flow path facing surface of the airfoil mount downstream of the trailing edge and are in fluid communication with the mount cooling plenum. The second film cooling holes cool the airfoil mount and any platform coupled thereto. The airfoil component can be additively manufactured.

Airfoil component for turbomachine component with platform cooling using airfoil coolant

A platform for a stator vane assembly includes a main body that extends between a forward end and an aft end. The platform further includes an opening that is defined within the main body. The opening is configured to receive an airfoil segment of the stator vane assembly. A forward portion of the main body extends between the forward end and the opening. An aft portion of the main body extends between the opening and the aft end. A cooling circuit is defined within the platform. The cooling circuit includes a first plenum defined in the forward portion, and at least one re-use plenum defined in the aft portion and separated from the first plenum. The cooling circuit further includes a connecting channel that fluidly couples the first plenum and the at least one re-use plenum.

Cooling circuit for a platform of a stator vane assembly

A turbine component includes a first structure exposed to a hot gas path and a second structure integral with the first structure but isolated from the hot gas path. A first fluid passage in the first structure delivers a thermal transfer fluid, e.g., air, through the first structure to cool the first structure. A second fluid passage is defined within the second structure and is in fluid communication with the first fluid passage. After heat transfer in the first structure, the thermal transfer fluid is hotter than a temperature of the second structure and thus increases the temperature of the second structure. The heat transfer to the second structure reduces a temperature difference between the first structure and the second structure that would, without heating, cause thermal stress between the structures. The heating of the second structure reduces the need for early maintenance and lengthens the lifespan of the component.

Turbine component with heated structure to reduce thermal stress

A turbine airfoil includes a body including a wall defining pressure and suction sides, and a leading edge extending between the pressure and suction sides. A cooling circuit inside the wall of the body includes at least one of: a) a suction side to pressure side cooling sub-circuit including a first cooling passage(s) extending from the suction side to the pressure side around the leading edge to a first plenum, and a plurality of first film cooling holes communicating with the first plenum and extending through the wall on the pressure side; and b) a pressure side to suction side cooling sub-circuit including second cooling passage(s) extending from the pressure side to the suction side around the leading edge to a second plenum, and a plurality of second film cooling holes communicating with the second plenum and extending through the wall on the suction side.

Turbine airfoil with leading edge cooling passage(s) coupled via plenum to film cooling holes, and related method

The present disclosure is directed to a turbomachine that includes a hot gas path component having an inner surface and defining a hot gas path component cavity. An impingement insert is positioned within the hot gas path component cavity. The impingement insert includes an inner surface and an outer surface and defines an impingement insert cavity and a plurality of impingement apertures fluidly coupling the impingement insert cavity and the hot gas path component cavity. A plurality of pins extends from the outer surface of the impingement insert to the inner surface of the hot gas path component.

Impingement insert for a gas turbine engine

An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.

Coolant delivery via an independent cooling circuit

A hot gas path component of an industrial machine includes an adaptive cover for a cooling pathway. The component and adaptive cover are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. The adaptive cover is positioned in the cooling pathway at the outer surface. The adaptive cover may include a heat transfer enhancing surface at the outer surface causing the adaptive cover to absorb heat faster than the outer surface.

Adaptive cover for cooling pathway by additive manufacture

A cooled structure has a leading edge, a trailing edge, a first side portion orthogonal to each of the leading and trailing edge, and a second side portion opposite the first side portion and substantially orthogonal to each of the leading and trailing edge. The cooled structure includes a substrate surface defined by boundaries including the leading edge, trailing edge, first side and second side portion. A first set of cooling channels beneath the substrate surface extends from a first set of inlets proximate to the first side portion to a first set of exits proximate to the second side portion. A second set of cooling channels beneath the substrate surface extends from a second set of inlets proximate to the second side portion to a second set of exits proximate to the first side portion. Each first inlet overlaps with an exit of the second set of exits.

Turbine shroud block segment with near surface cooling channels

An article includes a substrate and a structure including direct metal laser melted material of predetermined thickness attached to the substrate, the structure formed by providing and depositing a metal alloy powder to form an initial layer having a preselected thickness and shape including at least one aperture, melting the metal alloy powder with a focused energy source, transforming the powder layer to a sheet of metal alloy, sequentially depositing an additional layer of the metal alloy powder over the sheet of metal alloy, the additional preselected shape including an aperture corresponding to the aperture in the initial layer, and melting each additional layer of the metal alloy powder with the focused energy source, increasing the thickness of the sheet and forming at least one aperture having a predetermined profile, the article further including a passageway through the structure including the aperture and a corresponding metering hole.

Article

An article includes a substrate and a structure of additive manufacturing material of predetermined thickness attached to the substrate, the structure of additive manufacturing material formed by providing a metal alloy powder, forming an initial layer having a preselected thickness and a preselected shape including at least one aperture, with the metal alloy powder, sequentially forming an additional layer with the metal alloy powder over the initial layer, each of additional layers having an additional preselected thickness and an additional preselected shape including an aperture corresponding to the aperture in the initial layer, and joining each of the additional layers to the initial layer or any previously joined additional layers, forming a structure having a predetermined thickness and shape, and an aperture having a predetermined profile. The article includes a passageway through the structure including the aperture and a corresponding metering hole.

Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.

Turbine shroud including plurality of cooling passages

A rotary machine includes a rotatable member and a casing extending circumferentially over the rotatable member. The casing includes first and second target impingement surfaces. The cooling system includes first and second impingement plates. The first impingement plate is positioned over the first target impingement surface and at least a portion of the second target impingement surface. The first impingement plate defines a plurality of first impingement holes configured to channel a first flow of cooling fluid toward the first target impingement surface. The second impingement plate is positioned over the second target impingement surface. The second impingement plate defines a plurality of second impingement holes configured to channel a second flow of cooling fluid toward the second target impingement surface. A thickness of the casing in the first target impingement surface is different than a thickness of the casing in the second target impingement surface.

System and method for shroud cooling in a gas turbine engine

A hot gas path component of an industrial machine includes an adaptive cover for a cooling pathway. The component and adaptive cover are made by additive manufacturing. The component includes an outer surface exposed to a working fluid having a high temperature; a thermal barrier coating over the outer surface; an internal cooling circuit; and a cooling pathway in communication with the internal cooling circuit and extending towards the outer surface. The adaptive cover is positioned in the cooling pathway at the outer surface. The adaptive cover includes a heat transfer enhancing surface at the outer surface causing the adaptive cover to absorb heat faster than the outer surface, e.g., when a spall in a thermal barrier coating thereover occurs.

Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a forward end, an aft end, a first and second side, an outer surface facing a cooling chamber formed between the body and the turbine casing, and an inner surface facing a hot gas flow path for the turbine system. The turbine shroud may also include at least one collection plenum extending within the body between the forward end and the aft end. Additionally, the turbine shroud may include set of cooling passage(s) extending within the body. Each of the cooling passages of the set of cooling passage(s) may include an inlet portion in fluid communication with the cooling chamber, an outlet portion in fluid communication with the at least one collection plenum, and an intermediate portion fluidly coupling the inlet portion and the outlet portion.

Turbine shroud including cooling passages in communication with collection plenums

A hot gas path (HGP) component of an industrial machine includes primary and secondary cooling pathways. A body includes an internal cooling circuit carrying a cooling medium. A primary cooling pathway is spaced internally in the body and carries a primary flow of a cooling medium from an internal cooling circuit. A secondary cooling pathway is in the body and in fluid communication with an internal cooling circuit. The secondary cooling pathway is fluidly incommunicative and spaced internally from the primary cooling pathway. In response to an overheating event occurring, the secondary cooling pathway opens to allow a secondary flow of cooling medium through to the outer surface of the body and/or the primary cooling pathway. The primary flow flows in the primary cooling pathway prior to the overheating event, and the secondary flow of cooling medium does not flow until after an opening of the secondary cooling pathway.

Adaptively opening backup cooling pathway

Growing community of inventors

Greer, SC, United States of America

Benjamin Paul Lacy