General Electric Company

Ge Infrastructure Technology, LLC

Ge Vernova Infrastructure Technology LLC

General Electric Technology Gmbh

Ge Vernova Technology Gmbh

Zachary John Snider

Kurt Kramer Schleif

Matthew Troy Hafner

John McConnell Delvaux

Donald Shaw

Gregory Thomas Foster

Jeffrey Clarence Jones

Srikanth Chandrudu Kottilingam

Sandip Dutta

Brad Wilson VanTassel

Benjamin Paul Lacy

Stephen Paul Wassynger

Christopher Donald Porter

Mario Joseph Arceneaux

Gary Charles Liotta

Brian Denver Potter

Changjie Sun

Brad Wilson Vantassel

Travis J Packer

Sathyanarayanan Raghavan

Joseph Leonard Moroso

Daniel Robert Burnos

Lyndsay Marie Kibler

Claire Fridtjof Lang

John M Matthews

Gary Michael Itzel

Kirk Douglas Gallier

David Wayne Weber

Victor John Morgan

Richard Martin DiCintio

Brendon James Leary

Glenn Curtis Taxacher

Brian Gene Brzek

Prabhjot Singh

Jacob John Kittleson

James Albert Tallman

Joseph Anthony Weber

Robert Frank Hoskin

Andrew David Ellis

Ibrahim Sezer

John Ellington Greene

Kassy Moy Hart

Sylvain Pierre

Lana Maria Osusky

Michael Allen Ball

James Fredric Wiedenhoefer

Adam John Fredmonski

Robert William Davidoff

James Tyson Balkcum, Iii

Evan John Dozier

Elisabeth Kraus Black

Andrea Booher Kretschmar

Tyler Christopher Henson

Gautam Suresh Naik

Nathan Lee Brown

Allison Christine Gose

Burt Richard Skiba

Tonya Lynn Watkins

Tara Ashley Cole

Earl Thomas Dyson

Christopher West

Brad Wilson Van Tassel

John Mcconnell Delvaux

Joseph Antony Weber

Joseph Moroso

A cyclonic particle separator may include a housing including a cylindrical sidewall having a plurality of flow entry ports. A cover member closes a first end of the cylindrical sidewall, and a mounting member having a flow exit opening defined therethrough is at a second end of the cylindrical sidewall. At least one particle exit passage is defined in the housing. Each of the plurality of flow entry ports includes a flow directing surface angled to direct a gas flow from upstream of the housing to enter the housing in a tangential direction relative to the cylindrical sidewall, causing a cyclone vortex. The cyclone vortex acts to separate particles from the gas flow.

Gas turbine aerodynamic component cyclonic particle separator with multiple particle traps

A damper element and a vibration dampening system including a plurality of the stacked damper elements, are provided. The damper element(s) may be used in a body opening in a rotating blade in a turbine. The damper elements include a head member having an at least partially ramped surface, an opening defined through a center of the head member, and a plurality of flexible legs extending from the head member. Each flexible leg includes a radially extending body section having an end section, which has an outer end surface and an inner end surface. An elongated body extends through the opening in the head member. Centrifugal force causes the head member of adjacent damper elements to force the outer end surfaces of the flexible legs into frictional engagement with an inner surface of the body opening to dampen vibration.

Damper element with flexible legs for vibration dampening system for turbine blade

A vibration dampening system is provided for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening system includes a plurality of stacked damper pins within the body opening. Each damper pin includes an outer body having defined therein an inner opening and a plurality of side openings extending from the inner opening through an outer surface of the outer body; and an inner body that is nested and movable within the inner opening of the outer body. The inner body includes a first portion including a plurality of arms, each arm extending through a respective side opening of the outer body to frictionally engage the body opening. The end surfaces of the damper pins and the two bodies frictionally engage to dampen vibration.

Nested damper pin and vibration dampening system for turbine nozzle or blade

A stator vane includes a platform that defines an opening. The stator vane further includes an airfoil that has a leading edge, a trailing edge, a suction side wall, and a pressure side wall. The airfoil extends radially between a base and a tip. At least one of the base or the tip includes a protrusion. The protrusion extends into the opening of the platform such that the platform surrounds the protrusion of the airfoil. The stator vane further includes a braze joint disposed between and fixedly coupling the platform and the protrusion of the airfoil. The stator vane further includes a cooling circuit defined in at least one of the protrusion or the platform to cool the braze joint.

Cooling circuit for a stator vane braze joint

A damper element and a vibration dampening system including a plurality of the stacked damper elements, are provided. The damper element(s) may be used in a body opening in a rotating blade in a turbine. The damper elements include a head member having an at least partially ramped surface, and a plurality of flexible legs extending from the head member. Each flexible leg includes a radially extending body section having an end section, and the end section has an outer end surface and an inner end surface. Centrifugal force caused by rotation of the rotating blade cause the head member of an adjacent damper element to force the outer end surfaces of the plurality of flexible legs into frictional engagement with an inner surface of the body opening to dampen vibration. In certain embodiments, an elongated body may extend through an opening in the head member of the damper element(s).

Turbine shroud

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

A stator vane assembly includes a platform that defines an opening. The stator vane assembly further includes an airfoil segment that includes an airfoil and a boss. The airfoil includes a leading edge, a trailing edge, a suction side wall, and a pressure side wall. The airfoil extends radially between a base and a tip. The boss extends from at least one of the base or the tip of the airfoil. The boss is disposed in the opening of the platform. The stator vane assembly further includes a mechanical retention device that couples the platform to the boss of the airfoil segment.

Stator vane assembly having mechanical retention device

A vibration damping system includes a vibration damping element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade between the tip end and the base end thereof, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration damping element includes a plurality of stacked plate members within the body opening. Each plate member is in surface contact with at least one adjacent plate member to cause friction that dampens vibration of the nozzle or blade. The body opening has an inner dimension, and each plate member has an outer dimension sized to frictionally engage the inner dimension of the body opening to damp vibration. Plate members may each include a central opening therein, and a fixed elongated body or cable may extend through the central openings. The damping element may alternatively include a helical metal ribbon spring.

Vibration damping system for turbine nozzle or blade using stacked plate members

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 having an axially fixed position within the body opening, and a spring-suspended bearing member having a spring fixedly coupled to the base member at a first end of the spring and a bearing member coupled to a second end of the spring. With the 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 bearing surface to dampen vibration. The spring-suspended bearing member provides a friction-based vibration dampening interface that experiences a reduced impact of the centrifugal forces of the rotating blade by providing a counteracting force reduction using the spring.

A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.

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

An additively manufactured (AM) object may include a body including an opening in an exterior surface thereof, the opening having a shape and a first area at the exterior surface of the body. A mask may be positioned over the opening. The mask has the shape of the opening and a second area that is larger than the first area so as to overhang the exterior surface of the body about the opening. A plurality of support ligaments couple to the mask and the exterior surface of the body at a location adjacent to the opening to support a portion of the mask. A coating can be applied to the object, and the mask removed. The final AM object includes a plurality of ligament elements extending from the exterior surface of the body and through the coating adjacent the opening, each ligament element at least partially surrounded by the coating.

Additively manufactured object using mask over opening for coating

A hot gas path component assembly includes a first component portion that includes a first set of interlocking features and a second component portion that includes a second set of interlocking features mechanically coupled to the first set of interlocking features. A fill material is disposed at an interface between at least one surface of the first set of interlocking features and at least one surface of the second set of interlocking features. The fill material is disposed during a joining process. The second component portion is joined to the first component portion via both the fill material and the first and second sets of interlocking features.

Component with mechanical locking features incorporating adaptive cooling and method of making

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Simpsonville, SC, United States of America

Zachary John Snider