United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Hamilton Sundstrand Corporation

Other

Frederick M Schwarz

Gabriel L Suciu

Daniel Bernard Kupratis

Michael E McCune

William G Sheridan

William K Ackermann

Joseph Brent Staubach

Lawrence E Portlock

Brian D Merry

Wesley K Lord

Paul W Duesler

Shankar S Magge

Paul R Adams

Nathan A Snape

Christopher Marc Dye

Steven B Johnson

Jason Husband

Jorn Axel Glahn

Charles E Lents

Michael A Weisse

Robert E Malecki

David P Houston

Michael Winter

Glenn Levasseur

James D Hill

Alan H Epstein

Sean P Zamora

Lisa I Brilliant

Nigel David Sawyers-Abbott

Michael G McCaffrey

Daniel L Gysling

Jesse M Chandler

Paul R Hanrahan

Dilip M Shah

Kevin W Schlichting

Coy Bruce Wood

Matthew E Bintz

Robert H Perkinson

James T Roach

Karl L Hasel

Steven H Zysman

Bruce L Morin

Om Parkash Sharma

Thomas J Praisner

Matthew R Feulner

Michael Joseph Murphy

Charles R Watson

Becky E Rose

Robert J Morris

William R Graves

Thomas Gregory Tillman

James G Griffin

Brian M Fentress

Clifton J Crawley, Jr

Jesse W Clauson

Amy Rose Grace

Gregory A Kohlenberg

David J Candelori

Andrew P Berryann

Jeffrey D Ponchak

John W Golan

Matthew P Forcier

Timothy Dale

Stephen G Pixton

Zubair Ahmed Baig

Yuan Dong

Simon Pickford

David Gelwan

Gary F Chaplin

David M Nissley

J Walter Smith

James R Midgley

Jesse Walter Smith

Timothy B Winfield

Michael F Blair

John P Virtue

Peter G Smith

John T Schmitz

Subhradeep Chowdhury

Paul J Hiester

David A Welch

Mikhail B Gorbounov

Neal R Herring

Kurt R Heinemann

Steven H Taylor

Shari L Bugaj

Peter Gerard Smith

Mary Colby

Stuart S Ochs

Michael K Ikeda

Pedro David Laureano

David Louis Motto

Brian J Schuler

William E Rosenkrans

Taryn Narrow

Carroll V Sidwell

Rishon Saftler

C Bruce Wood

Steven D Sandahl

Wayne M Brown

A gas turbine engine includes a compressor section including a first compressor, a turbine section including a first turbine and a second turbine, a first shaft and a second shaft, the first shaft interconnecting the first turbine and the second compressor, and a geared architecture. The first shaft is supported on a first bearing in an overhung manner. A performance ratio is between 0.5 and 1.5.

Gas turbine engine with high speed low pressure turbine section and bearing support features

A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a geared architecture including a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the geared architecture.

Engine mount system for a gas turbine engine

A gas turbine engine according to an example of the present disclosure includes a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier and a ring gear including first and second portions. The first and second portions have axially opposed faces abutting one another at a radial interface.

Epicyclic gear train

A gas turbine engine according to an example of the present disclosure includes, among other things, propulsor means, first compression means, second compression means, reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input, first expansion means, and second expansion means. The reduction means includes an epicyclic gear system with a gear reduction. The gear system is straddle-mounted by first and second bearings on opposite sides of the gear reduction relative to an engine longitudinal axis.

An engine-driven cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for condensing a chilled air stream into liquid air for an aircraft use. The first air cycle machine includes a plurality of components operably coupled to a gearbox of a gas turbine engine and configured to produce a cooling air stream based on a first engine bleed source of the gas turbine engine. The second air cycle machine is operable to output the chilled air stream at a cryogenic temperature based on a second engine bleed source cooled by the cooling air stream of the first air cycle machine.

Cryogenic cooling system for an aircraft

A gas turbine engine includes a compressor section and a turbine section operably coupled to the compressor section. The gas turbine engine further includes a means for selectively releasing a cooling fluid flow produced at a cryogenic temperature and a plumbing system in fluid communication with the means for selectively releasing the cooling fluid flow. The plumbing system is configured to route the cooling fluid flow to one or more of the compressor section and the turbine section.

A ground-based cryogenic cooling system includes a means for cooling an airflow and producing chilled air responsive to a power supply. A liquid air condensate pump system is operable to condense the chilled air into liquid air and urge the liquid air through a feeder line. A cryogenic cartridge includes a coupling interface configured to detachably establish fluid communication with the feeder line and a cryogenic liquid reservoir configured to store the liquid air under pressure. The cryogenic cartridge can be coupled to a cryogenic liquid distribution system on an aircraft. The liquid air can be selectively released from the cryogenic cartridge through the cryogenic liquid distribution system for an aircraft use.

Propulsion system cooling control

An aircraft propulsion system is disclosed and includes a first gas turbine engine including a first input shaft driving a first gear system, a first fan driven by the first gear system, a first generator supported on the first input shaft and a fan drive electric motor providing a drive input to the first fan, a second gas turbine engine including a second input shaft driving a second gear system, a second fan driven by the second gear system, a second generator supported on the second input shaft and a second fan drive electric motor providing a drive input to the second fan and a controller controlling power output from each of the first and second generators and directing the power output between each of the first and second fan drive electric motors.

Aircraft hybrid propulsion fan drive gear system dc motors and generators

A gas turbine engine includes, among other things, a propulsor section including a propulsor hub, the hub including a hub diameter supporting a plurality of propulsor blades. A compressor section includes a first compressor and a second compressor. A turbine section includes a first turbine and a second turbine. A geared architecture interconnects the first turbine and the propulsor hub. The geared architecture includes a gear volume. A compressor inlet passage is disposed annularly about the geared architecture.

Gas turbine engine front section

A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the gear train.

A gas turbine engine according to an example of the present disclosure includes, among other things, a propulsor section including a propulsor supported on a propulsor shaft, a turbine section including a turbine shaft, a compressor section having a plurality of compressor hubs with blades driven by the turbine shaft about an engine axis, and an epicyclic gear train interconnecting the propulsor shaft and the turbine shaft. The epicyclic gear train includes a sun gear coupled to the turbine shaft, intermediary gears arranged circumferentially about and meshing with the sun gear, a carrier and a ring gear including first and second portions. The first and second portions have axially opposed faces abutting one another at a radial interface.

A gas turbine engine according to the present disclosure includes, among other things, a propulsor section including a propulsor having a plurality of blades, the plurality of blades having a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath, and a core engine including a first turbine that drives a first compressor and a second turbine that drives the propulsor section. A second inboard boundary of a core flowpath has a radius R1 defined at a first stage of a second compressor and has a radius R2 defined at a splitter rim that guides flow into the core flowpath.

Geared turbofan engine gearbox arrangement

A gas turbine engine turbine has a high pressure turbine configured to rotate with a high pressure compressor as a high pressure spool in a first direction about a central axis and a low pressure turbine configured to rotate with a low pressure compressor as a low pressure spool in the first direction about the central axis. A power density is greater than or equal to about 1.5 and less than or equal to about 5.5 lbf/cubic inches. A fan is connected to the low pressure spool via a speed changing mechanism and rotates in the first direction.

Geared turbofan engine with a high ratio of thrust to turbine volume

An example gas turbine engine includes a propulsor assembly consisting of a propulsor and a first turbine. An epicyclic gear train defines a gear reduction ratio of greater than 2.3. A weight of the propulsor assembly is less than 40 percent of a total weight of the gas turbine engine, excluding any nacelle. A first spool includes a first shaft that connects a first compressor and the first turbine. The first shaft drives the propulsor through the gear train to drive the propulsor at a lower speed than the first spool. A second spool includes a second shaft connecting a second compressor and a second turbine. A weight of the propulsor is greater than a weight of the first turbine.

Geared turbine engine with relatively lightweight propulsor module

A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio.

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Glastonbury, CT, United States of America

Frederick M Schwarz