United Technologies Corporation

Ultradent Products, Inc.

Raytheon Technologies Corporation

Rtx Corporation

Steven B Johnson

Gabriel L Suciu

Brian D Merry

Christopher Marc Dye

Frederick M Schwarz

Dan E Fischer

Neil Thomas Jessop

Peter M Allred

Barry Lee Hobson

Jonathan D Scoville

David Lawrence Margetts

Jorn Axel Glahn

Peter M Munsell

Curtis W Berger

Andrew J Murphy

Raymond J Bruchez, Jr

Keith S Brewer

Bradley C Johnson

Christopher M Dye

Ronald T Clawson

William G Hoop

James Hurchalla

William J Miller

Miguel A Garrido

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.

Engine mount system for a gas turbine engine

Wax-based compositions for making barrier layers used in oral treatment devices are thermally stable when formed into a flat sheet or three-dimensional article to a temperature of at least 45° C. and are plastically deformable at room temperature (25° C.). The wax-based compositions include a wax fraction homogeneously blended with a polymer fraction. The wax fraction includes at least one wax and the polymer fraction includes at least one polymer selected such that, when the at least one wax and at least one polymer are homogeneously blended together, they yield a wax-based composition having the desired properties of thermal stability and plastic deformability. Barrier layers and oral treatment devices made from such wax-based compositions are dimensionally stable to a temperature of at least 40° C. without external support and can be plastically deformed in a user's mouth to become at least partially customized to the size and shape of user's unique dentition.

Wax-based compositions, articles made therefrom, and methods of manufacture and use

Turbine engine systems and aircraft having such systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a drive shaft having at least a compressor section and a turbine section coupled thereto, a cryogenic fuel tank configured to supply a fuel to the combustor, and an expansion turbine mechanically coupled to the drive shaft, the expansion turbine configured to receive fuel from the cryogenic fuel tank and expand said fuel, wherein expansion of said fuel by the expansion turbine drives rotation of the expansion turbine to provide power input to the drive shaft.

Gas turbine engines having cryogenic fuel systems

A gas turbine engine includes, among other things, a propulsor section including a rotor, a gear train, a low spool and a high spool. A static structure includes a first case and a second case. A mount system includes a forward mount and an aft mount arranged in a plane containing an engine axis of rotation. The forward mount is secured to the first case. The aft mount is secured to the second case.

Oral treatment devices formed from wax-based compositions that are thermally stable when formed into a three-dimensional shape to a temperature of at least 45&#xb0; C. and plastically deformable at room temperature (25&#xb0; C.). The wax-based compositions include a wax fraction homogeneously blended with a polymer fraction. The wax fraction includes at least one wax. The polymer fraction includes at least one polymer selected such that, when the wax and polymer are homogeneously blended together, they yield a wax-based composition having the desired properties of thermal stability and plastic deformability. Oral treatment devices are dimensionally stable to a temperature of at least 40&#xb0; C. without external support and can be plastically deformed in a user's mouth to become at least partially customized to the size and shape of user's unique dentition and/or an appliance in a user's mouth.

A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.

Gas turbine engine with low stage count low pressure turbine and engine mounting arrangement

Wax-based compositions for making barrier layers used in oral treatment devices are thermally stable when formed into a flat sheet or three-dimensional article to a temperature of at least 45&#xb0; C. and are plastically deformable at room temperature (25&#xb0; C.). The wax-based compositions include a wax fraction homogeneously blended with a polymer fraction. The wax fraction includes at least one wax and the polymer fraction includes at least one polymer selected such that, when the at least one wax and at least one polymer are homogeneously blended together, they yield a wax-based composition having the desired properties of thermal stability and plastic deformability. Barrier layers in oral treatment devices made from such wax-based compositions are dimensionally stable to a temperature of at least 40&#xb0; C. without external support and can be plastically deformed in a user's mouth to become at least partially customized to the size and shape of user's unique dentition.

A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a first nacelle which at least partially surrounds a second nacelle and the fan rotor, the fan section configured to communicate airflow into the first nacelle and the second nacelle, a first turbine, and a second turbine followed by the first turbine. The first turbine is configured to drive the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.

Gas turbine engine with low stage count low pressure turbine

A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.

Gas turbine engine compressor arrangement

A gas turbine engine includes a spool along an engine centerline axis which drives a gear train.

A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low stage count low pressure turbine.

A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four (4) stages.

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Marlborough, CT, United States of America

Steven B Johnson