General Electric Company

Baker Hughes Oilfield Operations LLC

Vetco Gray Inc.

Dresser, Inc.

Christopher Edward Wolfe

Norman Arnold Turnquist

Robert Harold Cromer

Osman Saim Dinc

Frederick George Baily

Bharat S Bagepalli

David Robert Skinner

Deepak Trivedi

George Ernest Reluzco

Rahul Anil Bidkar

Rodrigo Rodriguez Erdmenger

Mark Edward Burnett

Neelesh Nandkumar Sarawate

Nathan Evan McCurdy Gibson

David Alan Caruso

Eric John Ruggiero

Bruce William Brisson

Quang Tue Nguyen Tran

Lawrence Edward Rentz

Biao Fang

Robert Arnold Judge

Nathan EvanMcCurdy Gibson

Bugra Han Ertas

Mahmut Faruk Aksit

Farshad Ghasripoor

Warren F Bessler

Gregory Ronald Gillette

Jinjie Shi

Steven Hector Azzaro

Roderick Mark Lusted

Richard Jon Chevrette

Omprakash Samudrala

Lawrence Donald Willey

Bodhayan Dev

Paul Thomas Marks

Brandon Wayne Miller

Daniel Alan Niergarth

Emad Andarawis Andarawis

William Dwight Gerstler

Willy Steve Ziminsky

Kripa K Varanasi

Kirk Douglas Gallier

Ambarish Jayant Kulkarni

Hendrik Pieter Jacobus De Bock

Robert Proctor

Thomas James Batzinger

Minyoung Lee

Xiaoqing Zheng

Victor John Morgan

Hua Xia

Daniel White Sexton

Steven Douglas Johnson

Matthew David Butts

Alfred Albert Mancini

Li Liu

Dennis Michael Gray

Michael Joseph Dell'Anno

Darren Lee Hallman

Kevin Thomas McCarthy

Yuri Alexeyevich Plotnikov

Donald E Woodmansee

John Francis Nolan

Andres Jose Garcia-Crespo

Azam Mihir Thatte

Anthony Holmes Furman

Vittorio Michelassi

Brian Gene Brzek

Mark Howard Giammattei

David Bruce Hall

Douglas Frank Beadie

Edward James Nieters

Kevin Robert Feldmann

Xiaolei Shirley Ao

Leonardo Ajdelsztajn

Henry William Boger

Mehmet Demiroglu

Robert Edward Deallenbach

Jason Edward Albert

Victor H Correia

Shyam Sivaramakrishnan

Gregory Allan Crum

Kenneth Lee Fisher

Kristopher John Frutschy

Kenneth Neil Whaling

Adolfo Delgado Marquez

Jamie Gamble

Paul Russell Wilson

Xuele Qi

Bala Corattiyil

Kevin Edward Hinderliter

Gary Dwayne Mandrusiak

Gabriele Mariotti

Dennis Paul Dry

Edward Arthur Dewhurst

Antonio Guijarro Valencia

James Albert Stares

Kevin Thomas McGovern

James Harvey Vogan

Ran Niu

Sergey Anatolievich Meshkov

A rotary machine seal assembly () includes seal segments () configured to circumferentially extend around a rotor () between a stator () and the rotor () of a rotary machine. One or more seal segments include a shoe plate (), a seal base (), and at least one intermediate member (). The shoe plate is disposed along the rotor. The seal base is disposed radially outward of the shoe plate. At least one intermediate member is coupled to and disposed between the seal base and the shoe plate. The at least one intermediate member includes an actuator portion () having first coefficient of thermal expansion and a constrictor portion () having a different, second coefficient of thermal expansion. The at least one intermediate member is configured to move the shoe plate from a radially outward position to a radially inward position with respect to the rotor responsive to the at least one intermediate member undergoing a temperature change.

Seal assembly for a rotary machine

A fuel nozzle valve includes a fuel nozzle valve liner having a channel with an opening for allowing fuel to flow therethrough and a seat. A plunger has a stud and a base substantially perpendicular to the stud, the plunger being configured to move relative to the fuel nozzle valve liner to seal or to open the opening of the fuel nozzle valve. The fuel nozzle valve further includes a metal resilient member configured to contact the base of the plunger and the seat of the fuel nozzle valve liner to seal the opening of the fuel nozzle valve when the plunger is moved to seal the fuel nozzle valve.

Fuel nozzle valve seals for high temperature

A seal assembly for a rotary machine is positioned between a rotating component and a stationary component of the rotary machine. The seal assembly includes a seal bearing face that opposes the rotating component and a slide device. The slide device is positioned between different fluid pressure volumes in the rotary machine. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing face includes feed ports. The feed ports extend through the seal bearing face to form an aerostatic portion of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component is a non-planar surface that, during rotating motion of the rotating component, forms an aerodynamic portion of the film bearing between the seal bearing face and the rotating component.

Aspirating face seal assembly for a rotary machine

A thermal management system for transferring heat between fluids includes a thermal transport bus through which a heat exchange fluid flows. Additionally, the system includes a heat source heat exchanger arranged along the bus such that heat is added to the fluid flowing through the heat source heat exchanger. Moreover, the system includes a plurality of heat sink heat exchangers arranged along the bus such that heat is removed from the fluid flowing through the plurality of heat sink heat exchangers. Furthermore, the system includes a bypass conduit fluidly coupled to the bus such that the bypass conduit allows the fluid to bypass one of the heat source heat exchanger or one of the heat sink heat exchangers. In addition, the system includes a valve configured to control a flow of the fluid through the bypass conduit based on a pressure of the fluid within the bus.

Thermal management system for transferring heat between fluids

A seal assembly to seal a gas turbine hot gas path flow at an interface of a combustor liner and a downstream component, such as a stage one turbine nozzle, in a gas turbine. The seal assembly including a piston ring seal housing, defining a cavity, and a piston ring disposed within the cavity. The piston ring disposed circumferentially about the combustor liner. The piston ring is responsive to a regulated pressure to secure sealing engagement of the piston ring and outer surface of the combustor liner. The seal assembly includes at least one of one or more sectional through-slots, bumps or channel features to provide for a flow therethrough of a high-pressure (P) bypass airflow exiting a compressor to the cavity. The high-pressure (P) bypass airflow exerting a radial force on the piston ring.

Pressure regulated piston seal for a gas turbine combustor liner

The subject matter described herein relate to a segmented piston seal system. The segmented piston seal includes a first semi-circular section (FSCS) that includes a first locking structure at opposite ends of the FSCS. The segmented piston seal includes a second semi-circular section (SSCS) that includes a second locking structure at opposite ends of the SSCS. The first and second locking structures are configured to lock the FSCS and the SSCS together to form a piston seal.

Segmented piston seal system

A turbine shroud is disposed between stages of stationary turbine nozzles. The turbine shroud includes arcuate shroud segments sealingly engaged with one another. Each shroud segment includes a bottom panel with a radially inner surface and a radially outer surface and opposite ends. Each end includes an end face, an end cutback face spaced from the end face, and an intermediate surface extending between the end face and the end cutback face to define a recess. One or more seals overlap the recess of a circumferentially adjacent pair of shroud segments to produce a sealed joint.

Sealing system for turbine shroud segments

A seal assembly for a rotary machine includes a seal bearing face that opposes a rotating component of the machine and a slide device coupled with the seal bearing face. The slide device axially moves toward the rotating component responsive to pressurization of the rotary machine. The slide device includes cross-over ports and the seal bearing includes feed ports. The feed ports extend through the seal bearing face to form aerostatic portions of a film bearing between the seal bearing face and the rotating component. The seal bearing face and/or the rotating component has a non-planar surface that, during rotating motion of the rotating component relative to the face of the seal bearing face, forms aerodynamic portions of the film bearing.

An ultrasonic flow meter system includes a conduit defining a channel, at least one pair of first transducers, at least one second transducer, and a processor. The pair of first transducers is mounted on the conduit and includes a transmitting transducer and a receiving transducer for generating a first responsive signal. The transmitting transducer and the receiving transducer are arranged on a chordal path. The second transducer is mounted on the conduit for generating a second responsive signal. The processor is configured to receive the first responsive signal and the second responsive signal, select one responsive signal according to a relationship of the first responsive signal and noise thereof and a relationship of the second responsive signal and noise thereof, and determine a flow rate of a flow medium according to the selected responsive signal. A method for measuring the flow rate of the fluid medium is also provided.

Ultrasonic flow meter system and method for measuring flow rate

A seal assembly that includes a rotatable seal component, a non-rotatable seal component, and a plurality of pairs of flexures. The non-rotatable seal component is disposed facing the rotatable seal component. The plurality of pairs of flexures is spaced apart from each other along a circumferential direction of the seal assembly. Each pair of the plurality of pairs of flexures has a center line and includes a first flexure and a second flexure disposed in a stressed condition such that a portion of the first flexure and a portion of the second flexure are in contact with each other. Further, the first end of the first flexure is inclined at a first angle relative to the center line and a first end of the second flexure is inclined at a second angle relative to the center line. Also, first end of the first flexure and a first end of the second flexure are coupled to each other and to the non-rotatable seal component.

Seal assembly

Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.

Turbine blade and method of forming blade tip for eliminating turbine blade tip wear in rubbing

An assembly for a turbomachine and a method for assembling a plurality of flow path components are presented. The assembly includes a plurality of flow path components disposed adjacent to one another, each flow path component having a forward surface, an aft surface, a pressure side surface, and a suction side surface. A seal channel is defined by the pressure side surface and the suction side surface of adjacent flow path components. The seal channel has an open forward end proximate to the forward surfaces and at least two rear ends proximate to the aft surfaces. The assembly includes a plurality of seal layers disposed within the seal channel such that one or more seal layers extend from the open forward end to a rear end and one or more other seal layers extend from the open forward end to another rear end.

Systems and methods for assembling flow path components

A seal assembly, for example, a face seal assembly for a machine such as a turbomachine, and an associated method of operating the seal assembly in the machine are disclosed. The seal assembly includes a rotatable seal component, a non-rotatable seal component, and a plurality of pairs of flexures. The non-rotatable seal component is disposed facing the rotatable seal component. The plurality of pairs of flexures is spaced apart from each other along a circumferential direction of the seal assembly. Each pair of the plurality of pairs of flexures includes a first flexure and a second flexure disposed in a stressed condition such that a portion of the first flexure and a portion of the second flexure are in contact with each other. Further, an end of the first flexure and an end of the second flexure are coupled to each other and to the non-rotatable seal component.

Seal assembly and an associated method thereof

A thrust bearing assembly for a machine includes a stator housing, a fluid film thrust bearing, and a ring bearing. The stator housing surrounds at least a segment of a rotor shaft and one or more runners on the rotor shaft that include a first runner surface and a second runner surface facing in opposite axial directions along the rotor shaft. The fluid film thrust bearing is axially held between a first stator surface of the stator housing and the first runner surface. The fluid film thrust bearing is configured to generate a fluid cushion that blocks the first runner surface from engaging the fluid film thrust bearing. The ring bearing is axially held between a second stator surface of the stator housing and the second runner surface. The ring bearing has an annular contact surface that engages the second runner surface to axially support the rotor shaft.

Machine thrust bearing assembly

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Niskayuna, NY, United States of America

Christopher Edward Wolfe