United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Jesse M Chandler

Gabriel L Suciu

Joseph Brent Staubach

Wesley K Lord

Brian D Merry

Marc J Muldoon

Nathan A Snape

Alan H Epstein

Neil J Terwilliger

Kurt J Sobanski

Michael E McCune

Matthew R Feulner

Steven M O'Flarity

T David Bomzer

Joseph Stack

William K Ackermann

Jon E Sobanski

James D Hill

Anthony R Bifulco

Charles E Lents

Steven H Zysman

Om Parkash Sharma

Robert E Malecki

Christopher J Hanlon

Stephen H Taylor

Federico Papa

William F Schneider

James A Kenyon

Andrew Hahn

Frederick M Schwarz

William G Sheridan

Daniel Bernard Kupratis

Thomas M Zywiak

Harold W Hipsky

Stephen Karl Kramer

Michael Winter

Jonathan F Zimmitti

Jayant Sabnis

Becky E Rose

Allan R Penda

David Lei Ma

Paul Attridge

Stephen G Pixton

Amanda Jean Learned Boucher

Amanda Jean Boucher

Jon Erik Sobanski

Gabriel L Sucui

A gas turbine engine and engine mount structure includes a core engine including a compressor section, a combustor section and a turbine section mounted within a core engine housing. The fan, the compressor section and the turbine section rotate about an axis of rotation. An outer nacelle surrounds the fan, and is spaced from the core engine housing to define a bypass duct. The fan delivers air into the bypass duct and into the core engine housing. The nacelle is formed with camber so as to be curved in a first plane away from the axis of rotation in a first lateral direction. An engine mount structure extends from the nacelle at an angle that is non-parallel and non-perpendicular to the first plane, and has a component in a lateral direction that is opposed to the first lateral direction. An aircraft is also disclosed.

Gas turbine engine mounted above wing and with camber

A propulsion system for an aircraft includes a gas generating core engine generates an exhaust gas flow that is expanded through a turbine section, a power turbine driven by the exhaust gas flow, a propulsor coupled to the power turbine, a hydrogen fuel system configured to supply hydrogen fuel to the combustor through a fuel flow path, a condenser arranged along the core flow path and configured to extract water from the exhaust gas flow, and an evaporator arranged along the core flow path receiving a portion of the water extracted by the condenser to generate a steam flow that is injected into the core flow path upstream of the turbine section.

Reverse flow hydrogen steam injected turbine engine

An aircraft propulsion system includes a thrust reverser assembly that includes a reverser door corresponding to a cooling air outlet duct for directing a cooling air flow from a condenser forward.

Thrust reverser in condenser exit duct

An aircraft propulsion system includes a series of condensers where water is condensed from the exhaust gas flow. Each of the series of condensers define a passage for exhaust gas flow such that water recovered from the exhaust gas flow drains at a downward angle in a direction of gravity through each of the series of condensers. A series of water separators separate the exhaust gas flow from water condensed in a corresponding one of the series of condensers and the water is transformed into a steam flow in an evaporator system for communication to the combustor.

Circumferential flow condenser arrangement for an aircraft propulsion system

An intercooler for a gas turbine engine can include a shell having a partial annular shape, the shell defining a duct comprising an inlet and an outlet, the shell defining a first flow path between the inlet and the outlet; a supply manifold disposed proximate the outlet of the duct and extending circumferentially around the shell; and an outlet manifold disposed proximate the inlet of the duct and extending circumferentially around the shell, the supply manifold in fluid communication with the outlet manifold through a heat transfer region in the duct.

Engine with intercooler

A turbine engine is provided that includes a fan section, a turbine engine core and a recovery system. The turbine engine core is configured to power the fan section. The turbine engine core includes a core compressor section, a core combustor section and a core turbine section. A centerline axis of the turbine engine core is offset from a centerline axis of the turbine engine. The recovery system includes an evaporator module and a condenser module. A core flowpath extends sequentially through the core compressor section, the core combustor section, the core turbine section, the evaporator module and the condenser module from an inlet into the core flowpath to an exhaust from the core flowpath.

Heat exchanger(s) for recovering water and/or heat energy from turbine engine combustion products

A heat exchanger has arcuate inlet and outlet manifolds and a plurality of tube banks, each tube bank coupling one of the inlet manifold outlets to an associated one of the outlet manifold inlets. Each tube bank partially nests with one or more others of the tube banks and has: a first header coupled to the associated inlet manifold outlet and the associated the outlet manifold inlet; a second header; and a plurality of tube bundles each having a first end coupled to the associated first header and a second end coupled to the associated second header. A flowpath from the each inlet manifold outlet passes sequentially through flowpath legs formed by each of the tube bundles in the associated tube bank to exit the tube bank to the associated outlet manifold inlet.

Gas turbine engine heat exchanger for annular flowpaths

A gas turbine engine includes a plurality of rotating components housed within a compressor section and a turbine section. A tap connects to the compressor section. A heat exchanger connects downstream of the tap. A cooling compressor connects downstream of the heat exchanger, and the cooling compressor connects to deliver air to at least one of the rotating components. A core housing has an outer peripheral surface and a fan housing defines an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is disposed within the at least one bifurcation duct.

Intercooled cooling air with heat exchanger packaging

An aircraft propulsion system includes a fan section that includes a fan shaft that is rotatable about a fan axis. The fan shaft includes a fan gear. The aircraft propulsion system also includes a boost turbine engine that includes a first output shaft that includes a first gear that is coupled to the fan gear. The boost turbine engine has a first maximum power capacity. The aircraft propulsion system further includes a cruise gas turbine engine that includes a second output shaft that includes a second gear that is coupled to the fan gear. The cruise turbine engine has a second maximum power capacity that is less than the first maximum power capacity of the boost turbine engine. The fan section produces a thrust that corresponds to power input through the fan gear from the boost turbine engine and the cruise turbine engine.

Multi core geared gas turbine engine

A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.

Systems and methods for hybrid electric turbine engines

A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

Intercooled cooling air tapped from plural locations

A gas turbine engine includes a harmonic drive driven by an actuator, a drive shaft driven by the harmonic drive, the drive shaft with a first drive gear and a second drive gear. A first variable vane stage with a first actuator gear to direct drive one of a multiple of variable vanes, the first actuator gear meshed with the first drive gear; and a second variable vane stage with a second actuator gear to direct drive one of a multiple of variable vanes, the second actuator gear meshed with the second drive gear.

Harmonic drive for shaft driving multiple stages of vanes via gears

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South Windsor, CT, United States of America

Jesse M Chandler