General Electric Company

Ge Infrastructure Technology, LLC

General Electric Technology Gmbh

Stephen Paul Wassynger

Zachary John Snider

Sandip Dutta

Srikanth Chandrudu Kottilingam

Benjamin Paul Lacy

Aaron Ezekiel Smith

Xiuzhang James Zhang

Mark Steven Honkomp

Shashwat Swami Jaiswal

Joseph Leonard Moroso

Nicholas Francis Martin

Carlos Alberto Collado

Kevin Lee Worley

Gary Michael Itzel

Kurt Kramer Schleif

Rohit Chouhan

Robert D Jones

Gary Charles Liotta

Brian Denver Potter

Brian Peter Arness

Joseph Anthony Weber

Andrew David Ellis

David Richard Johns

Ibrahim Sezer

Richard Ryan Pilson

Michael Ericson Friedman

Thomas Robbins Tipton

Spencer Aaron Kareff

Randall Richard Good

Andrew Paul Giametta

Jalindar Appa Walunj

Anthony Louis Giglio

James William Vehr

Anthony Constantine Thermos

Paul Lawrence Kalmar

Edward Durell Benjamin

Steven Eric Tomberg

Dwight Eric Davidson

Matthew Durham Collier

Jeffrey John Butkiewicz

Luke John Ammann

James Tyson Balkcum, Iii

Daniel Howard Tragesser

Benjamin Arnette Lagrange

Christopher Michael Penny

John Alan Eastman

Ajay Gangadhar Patil

Liming Xu

Anthony Aaron Chiurato

Michael David McDufford

Nick Martin

Emilio Fernandez

James Charles Gautreau

Stephen Joseph Balsone

Benjamin Arnette LaGrange

Matthew Scott Lutz

Steve Paul Byam

Stephen Robert Prince

Tushar S Desai

James Purdue Masso

Michael Reinker

Christopher Robert Kelly

Cj Silver

Poorna Krishnakumar

Jonathan David Crim

Robert David Jones

James Tyson Iii Balkcum

Joseph Moroso

Spencer A Kareff

Pilson Richard

A damper element for a vibration dampening system may be used in a body opening in a rotating blade in a turbine. The damper element includes a base member, and a spring-suspended bearing member having a disc spring fixedly coupled to the base member at a center of the disc spring, and a bearing member coupled to a first side of the disc spring at an outer portion thereof. The bearing member extends radially distal from the first side of the disc spring. With the disc spring in an elastically extended state under influence of a centrifugal force caused by rotation of the rotating blade at higher than a predefined rotational speed, the bearing member frictionally engages a first bearing surface to dampen vibration. The friction-based vibration dampening interface experiences a reduced impact of the centrifugal forces of the rotating blade by providing a counteracting force reduction using the spring.

Damper element with spring-suspended bearing member for vibration dampening system for turbine blade

At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a clock mounting location of the turbine component in a turbine.

Turbine components and methods of manufacturing

A measurement system for a gas turbine engine is provided. The measurement system comprises a sensor assembly. The measurement system also includes multiple sensors coupled to the sensor assembly. The sensor assembly is configured to be removably inserted within a space defined by a circumferential track embedded within an inner diameter of a casing of the gas turbine engine without having to disassemble the casing.

System and method for removably inserting a sensor assembly into a compressor casing

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

At least one turbine component for a gas turbine includes a base component formed by casting and an article. The base component includes a platform. The article on the upper surface of the platform is formed by additive manufacturing. The article has a proximal face sized and shaped to cover at least a portion of the upper surface of the platform of the turbine component and a contoured distal face opposite the proximal face. The contoured distal face has a contour surface serving as at least a portion of a hot gas path surface of the turbine component. The contour surface is arranged and disposed to provide a controlled flow pattern of a working fluid across the contour surface based on a mounting location of the turbine component in a turbine. Methods of manufacturing articles and turbine components are also disclosed.

A blade for a turbomachine includes an airfoil extending radially between a root and a tip with a tip shroud coupled to the tip of the airfoil. The tip shroud includes a platform having an outer surface extending generally perpendicular to the airfoil. The tip shroud also includes a forward rail extending radially outward from the outer surface of the platform. The forward rail is oriented generally perpendicular to a hot gas path of the turbomachine. A cooling cavity is defined in a central portion of the platform. The tip shroud also includes a cooling channel extending between the cooling cavity and an ejection slot formed in the forward rail. The ejection slot is positioned radially outward of the outer surface of the platform of the tip shroud.

Turbomachine blade cooling structure and related methods

A damper pin for damping adjacent turbine blades coupled to a rotor disk comprises a first elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the first elongated body. The first elongated body defines a slot that extends axially therethrough. The damper pin further includes a second elongated body having a generally arcuate top portion. The second elongated body is at least partially disposed within the slot and is slideably engaged in an axial direction with the first elongated body.

Damper pin having elongated bodies for damping adjacent turbine blades

A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length, which is less than the first axial length; and a turbine wheel defining a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The tip segment includes a tip segment material, the root segment includes a root segment material, and the turbine wheel includes a turbine wheel material, the root segment material and the turbine wheel material having a lower heat resistance and a higher thermal expansion than the tip segment material.

Turbine bucket assembly and turbine system

A turbine bucket according to various embodiments includes: a base; a blade coupled to the base and extending radially outward from the base, the blade including: a body having: a pressure side; a suction side opposing the pressure side; a leading edge between the pressure side and the suction side; and a trailing edge between the pressure side and the suction side on a side opposing the leading edge; a plurality of radially extending cooling passageways within the body; and at least one bleed aperture fluidly coupled with at least one of the plurality of radially extending cooling passageways, the at least one bleed aperture extending through the body at the trailing edge; and a shroud coupled to the blade radially outboard of the blade.

Turbine bucket having cooling passageway

A turbine nozzle includes an airfoil that extends in span from an inner band to an outer band where the inner band and the outer band define inner and outer flow boundaries of the turbine nozzle. At least one of the inner band and the outer band defines a plurality of cooling channels formed and a coolant discharge plenum beneath a gas side surface of the corresponding inner or outer band that is in fluid communication with the cooling channels. The coolant discharge plenum is formed within the inner band or the outer band downstream from the cooling channels and upstream from a plurality of coolant discharge ports.

Turbine nozzle with cooling channel coolant discharge plenum

This disclosure provides systems and methods for sealing flow path components, such as turbomachine airfoils, with a front-leaded seal. A seal channel is defined between a portion of the suction side surface of a first flow path component and a portion of the pressure side of a second flow path component. A seal is retained within the seal channel formed by the pressure side portion and the suction side portion and the seal channel defines a forward opening through which the seal is inserted during installation.

System and method for sealing flow path components with front-loaded seal

A turbine bucket includes a leading edge, a trailing edge, a root portion, and a tip portion. The turbine bucket also includes one or more cooling passages extending through a body of the turbine bucket from an inlet to an outlet. The cooling passages are configured to route a cooling flow of fluid through the turbine bucket. The turbine bucket further includes a plenum defined within the tip portion to receive the fluid from the outlet of the cooling passages for expulsion of the cooling flow of fluid into a main flow path via at least one outlet hole proximate the trailing edge of the turbine bucket.

Turbine bucket

A turbine blade having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may include a rib configuration that partitions the chamber and defines a flow passage having a first and a second side. The flow passage may include a port formed through the first side. A projection of a center axis of the port through the flow passage may define a strike point on the second side of the flow passage, and a backstrike recess may be positioned on the second side of the flow passage so to contain the strike point.

Structural configurations and cooling circuits in turbine blades

A turbine bucket for a gas turbine engine may include a platform, an airfoil extending radially outward from the platform, and a number of cooling passages defined at least partially within the airfoil. At least one of the cooling passages may extend radially to an outlet defined in an outer surface of the airfoil radially inward from a tip end of the turbine bucket.

Turbine bucket and method for cooling a turbine bucket of a gas turbine engine

An airfoil includes an outer surface having a leading edge, a trailing edge downstream from the leading edge, and a convex surface between the leading and trailing edges. A cavity is inside the outer surface, and a platform is connected to the outer surface and defines a top surface around at least a portion of the outer surface. A first plurality of trenches is beneath the top surface of the platform upstream from the leading edge, wherein each trench in the first plurality of trenches is in fluid communication with the cavity inside the outer surface. A first plurality of cooling passages provide fluid communication from the first plurality of trenches through the top surface of the platform.

Airfoil and a method for cooling an airfoil platform

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Simpsonville, SC, United States of America

Stephen Paul Wassynger