General Electric Company

Medivance, Inc.

Hartford Fire Insurance Compnay

Robert Proctor

Larry W Plemmons

Victor Hugo Silva Correia

Jeffrey Douglas Rambo

Jonathan Russell Ratzlaff

Jared Peter Buhler

Curtis Walton Stover

David A Di Salle

Christopher Charles Glynn

Steven Robert Brassfield

Robert Francis Manning

Gary Allen Carson

Robert Joseph Albers

Robert Carl Murray

Gregory Michael Laskowski

Gary Gruszecki

Timothy Deryck Stone

David R Linger

Julius John Montgomery

Byron Andrew Pritchard, Jr

Scott Alan Schimmels

Corey Bourassa

Monty Lee Shelton

Bhaskar Nanda Mondal

Steven Douglas Johnson

Rajesh Kumar

Michael J Epstein

Duane Howard Anstead

Gulcharan Singh Brainch

Kevin Samuel Klasing

Arnab Sen

Pradeep Hemant Sangli

Prasad Laxman Kane

Alan Roy Stuart

Thomas Kupiszewski

John Carl Glessner

Mark Leonard Hopper

John Christopher Brauer

Sesha Subramanian

John R Hess

Joseph Charles Albers

Christopher Jon Potokar

Wojciech Sak

Bradley Willis Fintel

Glen William Royal

Nathan Gerard Cormier

Edward P Brill

Paul Alexander Intemann

Mohamed Musthafa Thoppil

John William Hanify

Fred Y Choi

James Kevin Mount

Brandon Wayne Miller

Ronald Scott Bunker

Christopher Edward Wolfe

Kirk Douglas Gallier

Ambarish Jayant Kulkarni

Osman Saim Dinc

Mark Eugene Noe

Byron Andrew Pritchard

Nathan Evan McCurdy Gibson

Robert David Briggs

Craig Alan Gonyou

John Howard Starkweather

Dean Thomas Lenahan

Ning Fang

Jinjie Shi

Kevin Robert Feldmann

Steven Alan Ross

Donald Lee Gardner

David Scott Stapleton

Robert Charles Groves, Ii

Satoshi Atsuchi

Bala Corattiyil

Richard William Jendrix

David Andrew Hannwacker

Rafael Jose Ruiz

Gary Paul Moscarino

Daniel Fusinato

Jonathan Michael Rausch

Kenneth Martin Lewis

Roger Owen Barbe

Jeffrey Lee Mason

Gregory Alan White

George Joe-Kueng Chan

Andrew David Kemp

Mark Eden Zentgraf

Randall Brent Rydbeck

Bryan Keith Doloresco

Hai Buu Sam

Ray Harris Kinnaird

Scott Anthony Estridge

James Patrick Dolan

Gary A Gruszecki

Christopher Michael Thompson

Suresh Nukala Kumar

Jason Paul Hoppa

Thomas Matthew Doerflein

Scott Edward Farley

Marshall Scott Allen

A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.

Inducer assembly for a turbine engine

A back-end application computer server may access a location data store containing information about a set of locations to be visited, including location identifiers and location coordinates. The computer server may then prioritize the locations to be visited. A mobile unit data store may contain information about a set of mobile units, including mobile unit identifiers, mobile unit location coordinates, and mobile unit communication addresses. The computer server may then automatically assign each location to a mobile unit based on the location coordinates, the mobile unit location coordinates, at least one geo-fence, and said prioritization. Indications of assigned locations may be transmitted to each mobile unit via the associated mobile unit communication address, and electronic messages may be exchanged to support an interactive user interface display associated with assignments of locations to mobile units. According to some embodiments, the back-end computer server facilitates collection of location information from mobile devices.

Automatic assignment of locations to mobile units via a back-end application computer server

A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

Vehicle heat exchanger system including an inflatable operable with a cooling tube

A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

System for controlling blade clearances within a gas turbine engine

A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.

A patient temperature control system for automated temperature control according to a programmed protocol. In one aspect, at least one programmed protocol may be established for each of a plurality of patient thermal therapy phases. In turn, the temperature of a thermal exchange medium may be controlled upon the programmed protocol during each of the phases. A plurality of programmed protocols may be established, wherein a selected protocol may be utilized for automated temperature control during patient thermal therapy. The protocol may include a target patient temperature and/or a set duration for one or more of the phase of thermal therapy. The protocol may be user-definable and modifiable during therapy. In a multiphase configuration, automatic termination and initiation of successive phases may be selectively established by a user, based on target patient temperature data and/or set duration data on a phase-specific basis.

System and method for patient temperature control

Vehicle heat exchanger system including an inflatable member operable to press a cooling tube

A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.

An annular fluid flow control or metering device comprises: first and second annular plates disposed in an annular flow path, the first annular plate and second annular plates being made of different first and second materials, the first annular plate having a lower first coefficient of thermal expansion than a second coefficient of thermal expansion of the second annular plate, the first annular plate abutting or in contact with the second annular plate, the first annular plate including at least one first metering aperture, and the second annular plate being more thermally responsive than the first annular plate wherein the second annular plate being configured to radially grow and shrink to at least partly obstruct the at least one first metering aperture for metering or controlling a flow of fluid through the at least one first metering aperture.

Differential alpha variable area metering

An apparatus and method of cooling a hot portion of a gas turbine engine, such as a multi-stage compressor of a gas turbine engine, by reducing an operating air temperature in a space between a seal and a blade post of adjacent stages by routing cooling air through an inlet in the vane, passing the routed cooling air through the vane, and emitting the routed cooling air into the space.

Gas turbine engine with vane having a cooling inlet

An apparatus for a turbine engine comprising an outer casing, an engine core provided within outer casing and having a at least one set of blades, and through which gasses flow in a forward to aft direction, an outer drum located within the outer casing to define an annular cavity. A set of seals extending between the first surface and the second surface to define at least one cooled cavity within the annular cavity.

Turbine engine with annular cavity

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

An assembly for a turbine engine comprising a plurality of circumferentially arranged segments having first and second confronting end faces. The first and second confronting end faces include a multi-channel spline seal assembly. The multi-channel spline seal assembly includes at least a first and second channel wherein confronting first or second channels can receive at least one spline seal.

Spline for a turbine engine

A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.

Turbine engine and particle separators therefore

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West Chester, OH, United States of America

Robert Proctor