General Electric Company

General Electric Deutschland Holding Gmbh

General Electric Company Polska Sp. Z O.o.

Scott Alan Schimmels

Jeffrey Douglas Rambo

Brandon Wayne Miller

Arthur William Sibbach

Steven Douglas Johnson

Daniel Alan Niergarth

Ravindra Shankar Ganiger

Craig Alan Gonyou

Timothy Richard DePuy

Steven B Morris

Jeffrey Donald Clements

Robert Proctor

Ashish Sharma

Adam Tomasz Pazinski

Subramani Adhiachari

Hiranya Kumar Nath

Rajesh Kumar

Erich Alois Krammer

Nicholas M Daggett

Mustafa Dindar

Tomasz Jan Bulsiewicz

Piotr Jerzy Kulinski

Jeffrey S Spruill

Bradford Alan Tracey

Anand Roday

Matthew Kenneth MacDonald

Deepak Trivedi

Rahul Anil Bidkar

Scott Hunter

Patrick Michael Marrinan

Aaron Michael Dziech

Atanu Saha

Thomas Kupiszewski

Narendra Anand Hardikar

Eyitayo James Owoeye

Mohan Kannaiah Raju

Sesha Subramanian

Arvind Namadevan

Antonio Guijarro Valencia

Thomas Joseph Lipinski

Robert R Rachedi

Thomas DeWitt Woodrow

Paul Alexander Intemann

Paul Joseph Kreitzer

Kenneth Jay Moore

Christopher Michael Thompson

Michael Everitt Isenberg

Prasant Bilaiya

Vilas Kawaduji Bokade

Nicholas Joseph Kray

Bugra Han Ertas

Randy M Vondrell

Paul Hadley Vitt

Praveen Sharma

Rodrigo Rodriguez Erdmenger

Eric Richard Westervelt

John Carl Glessner

Veeraraju Vanapalli

Kevin Richard Graziano

Travis J Packer

William Joseph Bowden

Prateek Jalan

Pradeep Hemant Sangli

David Perveiler

Richard William Jendrix

Vaishnav Raghuvaran

James Michael Hoffman

Santosh Kumar Potnuru

Maciej Krzysztof Grunwald

Michael Alan Hile

Matthew Thomas Beyer

Vishnu Das K

Victor Moreno Patan

Evren Özcan

Brian Gregg Feie

Daniel Fusinato

Jeffrey D Carnes

Michael John Simonetti

Keith Blodgett

Brandon Christopher Clarke

Joseph Herbert Fields

Thomas Ryan Wallace

Miroslaw Czarnik

Sergio Filippi

James Hamilton Grooms, Iii

Christopher N Delametter

Lukasz Maciej Janczak

Eric Barre

Dennis Robert Jonassen

Leonardo Aguilar Willys

Vishnu Vardhan Tatiparthi

Ryan Nicholas Porter

Andrew Kevin Winn

Pawel Zdrojewski

Michael G Chenery

Mehmet Cem Apaydin

Rajani Bhanu Poornima M

Pankaj Sharma

Tran Quang Tue Nguyen

Yu-Liang Lin

A gas turbine engine is provided. The gas turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (A) in square inches; wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (Fn) in pounds, and a corrected specific thrust, wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific determined as follows: Fn×EGT/(A×1000).

Gas turbine engine

A heat exchanger positioned within an annular duct of a gas turbine engine is provided. The heat exchanger extends substantially continuously along the circumferential direction and defining a heat exchanger height equal to at least 10% of a duct height. An effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for an operating condition of the gas turbine engine. The heat exchanger includes a heat transfer section defining an acoustic length (L), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the operating condition.

Gas turbine engine having a heat exchanger located in an annular duct

A turbine engine including a fan having a plurality of fan blades, a turbo-engine positioned downstream of the fan and having a core inlet, an engine intake that extends to the core inlet, and a variable engine intake system. Air enters the turbine engine through the engine intake. The variable engine intake system includes a plurality of wind condition sensors for sensing wind conditions about the turbine engine, and a controller. The plurality of wind condition sensors includes a first wind condition sensor on a first side of the turbine engine and a second wind condition sensor on a second side of the turbine engine. The controller adjusts the engine intake based on the wind conditions about the turbine engine from the first wind condition sensor and the second wind condition sensor.

Turbine engine having a variable engine intake system

A method of detecting an airflow fault condition in a gas turbine engine, the method including: operating the gas turbine engine with a thermal transport bus having an intermediary heat exchange fluid flowing therethrough; determining a performance characteristic of the intermediary heat exchange fluid in the thermal transport bus is outside of a predetermined range, wherein the performance characteristic includes a temperature, a pressure, a flowrate, or a combination thereof; and indicating an airflow fault condition in response to determining the performance characteristic is outside of the predetermined range.

System and method of detecting an airflow fault condition

A gas turbine engine including a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel producing combustion gases. The steam line is fluidly coupled to the core air passage at a position downstream of the combustor to receive a portion of the combustion gases. A conduit thermally coupled to an external surface of an aircraft may be fluidly coupled to the steam line to receive the combustion gases and to heat the external surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gases and to condense the water vapor of the combustion gases. At least one nozzle may be fluidly coupled to the water vapor condenser to inject the condensed water into the core air passage.

Ice protection systems for aircraft fueled by hydrogen

A turbine engine for an aircraft. The turbine engine includes a combustor fluidly coupled to a fuel delivery assembly to receive fuel from the fuel delivery assembly. The fuel is injected into the combustor and combusted in the combustor to generate combustion gases. A condenser is located downstream of a turbine to receive the combustion gases and to condense water. The fuel heat exchanger is thermally coupled to the condenser to receive heat from the water condensed by the condenser. The fuel heat exchanger is located in the fuel delivery assembly to receive the fuel and to transfer the heat received from the water to the fuel. The boiler is located downstream of the fuel heat exchanger. The boiler receives the water and is fluidly connected to the combustor to receive the combustion gases and to boil the water to generate steam.

Turbine engine including a steam system

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 gas turbine engine having a compressor section, a combustion section, and a turbine section in serial flow arrangement to define a diffuser cavity between the compressor section and the combustor section, and an aft cavity. A compressor discharge pressure duct fluidly draws air from the diffuser cavity, passes it through a heat exchanger to cool the air, and then supplies the cooled air to the aft cavity.

Cooling air delivery system and methods thereof

A self-cleaning conduit for a hydrocarbon fluid. The conduit includes a tube and a mesh. The tube has an interior surface defining a flow passage for the hydrocarbon fluid. The mesh is positioned within the flow passage to abut the interior surface and movable along the interior surface to break-up deposits on the interior surface. The mesh is characterized by a mesh activation parameter (MAP) from one ten thousandths to six tenths.

Self-cleaning conduits for hydrocarbon fluids

A method of operating a gas turbine engine comprising: extracting a flow of air from a compressor section of the gas turbine engine into a first conduit; flowing the extracted flow of air through the first conduit to a first location at a turbine section of the turbine section, wherein a second conduit is in fluid communication with the turbine section at a second location; flowing a heat transfer fluid to a first heat exchanger positioned in thermal communication with the flow of air through the first conduit, the heat transfer fluid in thermal communication with the extracted flow of air through the first conduit via the first heat exchanger; and modulating, via a flow control device, a portion of the flow of air extracted from the first conduit to the second conduit downstream of the first heat exchanger.

Gas turbine engine with a fluid conduit system and a method of operating the same

A turbine engine having a rotor rotatable about a rotational axis, a stator, a plurality of circumferentially spaced bleed air passages, and an inducer. The plurality of circumferentially spaced bleed air passages being located between an axially adjacent set of vanes of the stator and blades of the rotor. The inducer including a nozzle passage fluidly coupling a nozzle inlet of the inducer to a nozzle outlet of the inducer.

Turbine engine having a compressor with an inducer

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Miamisburg, OH, United States of America

Scott Alan Schimmels