General Electric Company

Energy Recovery, Inc.

General Electric Deutschland Holding Gmbh

Ge Vernova Technology Gmbh

Neelesh Nandkumar Sarawate

Victor John Morgan

Christopher Edward Wolfe

David Wayne Weber

Deepak Trivedi

Changjie Sun

Ananda Barua

Jonathan Dwight Berry

Kevin Weston McMahan

Xiaoqing Zheng

Farshad Ghasripoor

Steven Douglas Johnson

Rahul Anil Bidkar

Azam Mihir Thatte

Larry Steven Rosenzweig

David Deloyd Anderson

Norman Arnold Turnquist

Venkat Subramaniam Venkataramani

Matthew Troy Hafner

Rodrigo Rodriguez Erdmenger

Ravindra Shankar Ganiger

Srikanth Chandrudu Kottilingam

Benjamin Paul Lacy

Gary Michael Itzel

Michael John Hughes

Glen Harold Kirby

Kirk Douglas Gallier

William Edward Adis

Gregory Thomas Foster

Darrell Glenn Senile

Ronald James Chila

Bodhayan Dev

Jason Edward Albert

Sathyanarayanan Raghavan

Ibrahim Sezer

Russell Pierson DeForest

Edip Sevincer

James Elliott McLean, Jr

Joseph Michael Marchetti

Kenneth Martin Lewis

Omprakash Samudrala

Kuo-Chiang Chen

Behzad Zamanian Yazdi

Anthony Christopher Marin

Stephen Francis Bancheri

Christopher Walter Falcone

Surinder Singh Pabla

Thomas Earl Dyson

Jacob John Kittleson

Jinjie Shi

Bradley Taylor Boyer

Narendra Anand Hardikar

Michael Dennis Mack

Eric John Ruggiero

Robert Alan Frederick

Mehmet Demiroglu

John Ellington Greene

Prateek Jalan

Nicholas Edward Antolino

Martin James Jasper

Antonio Guijarro Valencia

Julius John Montgomery

Wojciech Sak

Robert Gerard Baran

Benjamin Scott Huizenga

Jason Ray Gregg

John Patrick Pollinger

Robbert Christiaan Pannekeet

Jose Maria Rey Villazon

Yu Mukherjee

Michael John Brown

Robert Carl Meyer

David Benjamin Helmer

Keith Michael Parker

Kevin Randall McManus

Stephan Priebe

Vivek Raja Raj Mohan

Kevin Weston Mcmahan

Russell Pierson Deforest

An engine component with an abradable material and treatment is disclosed herein. An example engine component includes a substrate having a first thickness and defining at least a first substrate surface, the substrate extending along an axial direction, an abradable material on the first substrate surface, the abradable material defining a first abradable material surface, a second abradable material surface spaced radially apart from the first abradable material surface and defining a second thickness, and a treatment, the treatment extending from the first abradable material surface through at least a portion of the first thickness of the substrate.

Engine component with abradable material and treatment

A system includes a pressure exchanger (PX), a first heat exchanger, and a second heat exchanger. The PX is configured to receive a first fluid and a second fluid, exchange pressure between the first fluid and the second fluid, and output the first fluid and the second fluid. The first heat exchanger is configured to receive the first fluid from a first gas cooler and the second fluid from a second gas cooler, exchange first heat between the first fluid and the second fluid, and output the first fluid and the second fluid. The second heat exchanger is configured to receive heat exchanger output from the first heat exchanger and evaporator output from an evaporator, exchange second heat between the heat exchanger output and the evaporator output, and provide the heat exchanger output to the PX and the evaporator output to the compressor.

Refrigeration and heat pump systems with pressure exchangers

A system includes a pressure exchanger (PX) configured to receive a first fluid at a first pressure and a second fluid at a second pressure and exchange pressure between the first fluid and the second fluid. The system further includes a condenser configured to provide corresponding thermal energy from the first fluid to a corresponding environment. The system further includes a first ejector to receive a first gas and increase pressure of the first gas to form the second fluid at the second pressure. The first ejector is further to provide the second fluid at the second pressure to the PX.

A seal for a rotor is provided. The rotor defines an axial direction, a circumferential direction, and a radial direction. The seal includes a first flexible element coupled to the rotor. The first flexible element extends in a first direction that is within forty five degrees of the axial direction.

Seal for a rotor

A seal assembly for a rotary machine, such as a turbine engine, may include a seal rotor comprising a rotor face, a seal slider comprising a slider face, a seal stator, wherein the seal slider is slidably coupled to the seal stator, and wherein the slider face and the rotor face define a primary seal. The seal slider may be configured to slidably engage and retract the slider face with respect to the rotor face. The seal assembly may further include a secondary seal disposed between the seal slider and the seal stator. The secondary seal may be configured to compress and rebound and/or to expand and rebound, over at least a portion of a range of motion of the seal slider.

Seal assemblies for turbine engines and related methods

A fluid handling system includes a pressure exchanger (PX) configured to receive a first fluid at a first pressure and a second fluid at a second pressure and exchange pressure between the first fluid and the second fluid. The system further includes a condenser configured to provide corresponding thermal energy from the first fluid to a corresponding environment. The system further includes a receiver to receive the first fluid output by the PX. The receiver forms a chamber to separate the first fluid into a first gas and a first liquid. The system further includes a first booster to increase pressure of a portion of the first gas to form the second fluid at the second pressure and provide the second fluid at the second pressure to the PX.

A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.

Curved seal for adjacent gas turbine components

An abradable insert for a gas turbine engine, the abradable insert including: a base layer; a lattice layer connected to the base layer, wherein the lattice layer comprises a series of walls that define a plurality of cells; and a sheet layer connected to the lattice layer on an opposite side on the lattice layer from the base layer, wherein the sheet layer is curved and includes a direction of concavity that points away from the base layer, wherein the lattice layer and the sheet layer are integrally formed together and are a monolithic piece of material.

Abradable insert with lattice structure

A system for a turbine blade tip to address wear during rubbing with a shroud, and also tip rail cooling, is provided. The turbine blade tip includes a tip rail and cooling passage(s) extending through a radially outer end surface thereof, providing direct cooling to the tip. The tip rail may include tip rail cooling inserts. The radial outer end surface of the tip rail includes a first portion radially inward of a second portion thereof. An abrasive layer extends along the first portion adjacent the cooling passage(s), and may include a matrix alloy having a plurality of cubic boron nitride (cBN) particles and a plurality of ceramic particles embedded therein. The abrasive layer extends radially outward of the second portion of the radial outer end surface. The system also may include a shroud including an abradable coating thereon.

System for addressing turbine blade tip rail wear in rubbing and cooling

A flexible seal is used to seal between two adjacent gas turbine components. The flexible seal includes at least one metal ply having a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially, and optionally radially, offset from the forward end. A plurality of relief cuts is defined through the at least one metal ply between the forward end and the aft end to increase flexibility and improve sealing in seal slots that are radially offset from one another.

Curved seal with relief cuts for adjacent gas turbine components

An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.

Integrated combustor nozzles with continuously curved liner segments

Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including a slot including one or more slot segments located in an end face and a seal assembly disposed in the slot. The seal assembly including a plurality of seal segments forming at least one T-junction where a first seal segment intersects a second seal segment and at least one shim seal. The plurality of seal segments define at least one chute gap. The at least one shim seal disposed in a slot proximate the at least one T-junction of the plurality of seal segments. The at least one shim seal positioned on a sidewall of the second seal segment and extending a partial length of the sidewall. The at least one shim seal seals the at least one chute gap to prevent a flow therethrough of a gas turbine hot gas path flow.

Seal assembly for chute gap leakage reduction in a gas turbine

A turbine system including a sealing component is presented. The sealing component is positioned in a gap between adjacent turbine components of the turbine system. The sealing component includes a metallic shim including a high-temperature-resistant alloy in a single crystal form. A turbine shroud assembly including the sealing component is also presented.

Turbine systems with sealing components

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

Growing community of inventors

Niskayuna, NY, United States of America

Neelesh Nandkumar Sarawate