Hamilton Sundstrand Corporation

Rtx Corporation

Raytheon Technologies Corporation

Rockwell Collins, Inc.

Utc Aerospace Systems Wroclaw Sp. Z O.o.

Joseph E Turney

Ram Ranjan

Robert H Dold

Abbas A Alahyari

Jagadeesh Kumar Tangudu

John H Whiton

Kimberly Rae Saviers

Kathryn L Kirsch

Brian St Rock

Neil J Terwilliger

Andrzej Ernest Kuczek

Michael K Ikeda

Joseph Brent Staubach

Neal R Herring

Matthew B Kennedy

Thomas M Yun

Christopher Britton Greene

Eric Surawski

Sean C Emerson

James Streeter

Paul Attridge

Alexandru Cadar

Raphael Mandel

Richard Andrew Himmelmann

Donald E Army

Louis J Bruno

Zissis A Dardas

Matthew Robert Pearson

Christopher J Hanlon

Paul Papas

Dmytro Mykolayovych Voytovych

Randolph Carlton Mcgee

Paul M D'Orlando

Peter A T Cocks

Matthew Pess

John T Schmitz

Peter Cocks

Justin R Urban

Lawrence E Zeidner

David Saltzman

Ryan Matthew Kelley

Robert R Hebert

Allen Murray

Robert C Roy

Jaroslaw Rubalewski

Andressa L Johnson

Tomasz Meczkowski

Hubert Siudzinski

James M Donohue

Sherif M Kandil

Jakub Drzewiecki

Kimberly R Saviers

Peter At Cocks

Paul D'ORLANDO

Aircraft may include electric motors. The aircraft electric motors may include a rotor assembly comprises an outer diameter portion, and inner diameter portion, and an end portion, arranged to define a stator cavity, and a rotor hub configured to connect to a shaft of the aircraft electric machine, a stator assembly arranged within the stator cavity, and at least one fan assembly arranged in the rotor assembly and configured to induce a cooling flow through the stator cavity.

Electric machine having rotor with integrated fan

A gas turbine engine includes a main compressor section and a main turbine section. A cooling air supply system cools a location in at least one of the main compressor section and the main turbine section. The cooling air supply system includes a tap for tapping cooling air compressed by the main compressor section, connected for passing the cooling air through a heat exchanger and to a boost compressor, and then to the cooling location in the at least one of the main compressor section and the main turbine section. A fuel supply system has a fuel tank for delivering fuel to a fuel pump. At least one valve for selectively returning fuel downstream of the main pump back to an upstream location. At least one return turbine drives at least one fluid moving device in the air cooling system.

Excess fuel flow to drive turbine

Stators for aircraft electric motors include a cantilever structure having a supported end and an unsupported end, wherein the cantilever structure includes an inlet support manifold and an outlet support manifold arranged at the supported end and a plurality of cooling plates extending from the inlet support manifold and the outlet support manifold to the unsupported end. A plurality of coils are arranged between and in thermal contact with the cooling plates and a core passes through the plurality of coils and the plurality of cooling plates. Each cooling plate defines a cooling channel that fluidly couples the inlet support manifold and the outlet support manifold, and the coils and the core are structurally supported by the plurality of cooling plates in a cantilevered manner at the supported end.

Electric machine having multi-function cooling channels

Cooling systems include a cold sink having a number of heat load cooling paths and a heat load associated with each cooling path. An inlet is configured to supply a cooling fluid into the cold sink and an outlet is configured to receive the cooling fluid after passing through the plurality of heat load cooling paths of the cold sink. A pressure regulating element is arranged along each cooling path, each pressure regulating element arranged between the inlet and the heat load along each cooling path and configured to cause a pressure drop in the cooling fluid prior to passing the cooling fluid to each heat load. The pressure drop caused by each pressure regulating element is the same and is a pressure drop greater than a maximum pressure drop across each heat load of a system without such pressure regulating elements.

Stable pumped two-phase cooling

A heat exchanger includes a plurality of longitudinally-extending first channels and a plurality of second channels fluidly isolated from the plurality of first channels. Each first channels includes a plurality of spiraling internal fins and a plurality of external fins. The internal fins extend from and are integrally formed with the internal walls of the first channel. The external fins connect extend from and are integrally formed with the external walls of the first channels, connecting channels together. The plurality of second channels is defined in part by external walls of the plurality of first channels and the plurality of external fins.

Heat exchanger with heat transfer augmentation features

A heat exchanger having: front and aft ends; heat exchanger cores in an annular loop that define circumferential gaps between adjacent pairs of the cores, the cores, individually or as axially aligned sets, extend from the front to aft ends and have facing inlet sides and circumferentially facing outlet sides configured such that the inlet sides and the outlet sides from the adjacent pairs of the cores face into the same circumferential gaps; and core guide vanes disposed in the circumferential gaps, the core guide vanes have an aft portion that extends from the front end to the aft end of the heat exchanger, wherein: at the front end the heat exchanger, the core guide vanes are closer to the outlet side of the cores; and at the aft end the heat exchanger, the core guide vanes are closer to the inlet sides of the cores.

Annular arrangement of heat exchangers

A turbine engine assembly includes a condenser assembly arranged along the core flow path to extract water from the exhaust gas flow, and an evaporator assembly where thermal energy from the exhaust gas flow is communicated to the water extracted by the condenser assembly to generate a steam flow for injection into the core flow path. The evaporator assembly splits steam generation and cooling functions to increase efficiencies of each function.

Split evaporator for steam injection turbine engine

A heat exchanger having: an inlet header having inlet tubes stacked against the first side of the heat exchanger; an outlet header having outlet tubes stacked against the second side of the heat exchanger, first inlet and outlet tubes have a same length as each other, second inlet and outlet tubes have the same length as each other and are longer than the first inlet and outlet tubes, and third inlet and outlet tubes have a same length as each other and are longer than the second inlet and outlet tubes; core channels extend from the first side to the second side of the heat exchanger, the core channels connect the inlet tubes to the outlet tubes such that: the first inlet tube and third outlet tube are connected; the second inlet tube and second outlet tube are connected; and the third inlet tube and first outlet tube are connected.

Crossflow heat exchanger with stacked distribution tubes

A header for a high-pressure heat exchanger includes a first high-pressure transition section with inlets for multiple first high-pressure flow channels that are spaced from one another in a radial direction and collectively arranged in a substantially circular shape. The inlets for the multiple first high-pressure flow channels on a radially outer edge of the first high-pressure transition section are spaced further apart in a circumferential direction from adjacent inlets of the multiple first high-pressure flow channels than radially inward inlets are spaced from adjacent radially inward inlets of the multiple first high-pressure flow channels. The header also includes multiple first high-pressure flow channels extending from the first high-pressure transition section to a second-high pressure transition section that is configured to divide each of the multiple first high-pressure flow channels into at least two first high-pressure sub-flow channels.

Header for high-pressure heat exchanger

A turbine engine assembly an inter-turbine burner that is disposed between at least two of a plurality of turbine stages where an additional amount of fuel is mixed with an exhaust gas flow to generate a reheated gas flow. A condenser extracts water from the reheated gas flow and an evaporator system generates a steam flow from at least a portion of water that is extracted by the condenser for injection into the core airflow.

Inter-turbine burner in recuperation cycle engine

Aircraft fuel system including a fuel vessel containing a non-mixture fuel. A protective vessel is arranged about the fuel vessel such that the fuel vessel is contained within the protective vessel and a protective space is defined between an outer surface of a vessel wall of the fuel vessel and an inner surface of a vessel wall of the protective vessel. At least one mounting structure fixedly positions the fuel vessel within the protective vessel. A fuel consumption device configured to consume the non-mixture fuel. A fuel output fluidly connects an interior of the fuel vessel to the fuel consumption device, the fuel output being fluidly isolated from the protective space. A relief output fluidly connects the protective space to a relief flow path, the relief output and relief flow path configured to vent gas from the protective space and remove any non-mixture fuel from the protective space.

Fuel storage leak mitigation for aircraft

A combustor for a detonation engine includes a radially outer wall extending along an axis; a radially inner wall extending along the axis, wherein the radially inner wall is positioned at least partially within the radially outer wall to define an annular detonation chamber having an inlet for fuel and oxidant and an outlet; a cooling flow passage defined along at least one of the radially outer wall and the radially inner wall and comprising at least two axially spaced cooling flow passage sections, whereby a different cooling rate can be implemented in the at least two axially spaced cooling flow passage sections.

Cooling for detonation engines

An aircraft propulsion system includes a core engine for generating an exhaust gas flow that is used to generate a power output. A condenser assembly extracts water from the gas flow and stores water in a water storage tank. A cooling system maintains water stored in the storage tank at a temperature within a predefined range.

Water storage precooling and water cycle chiller

Aircraft electric motors are described. The aircraft electric motors include a motor unit having a rotor and a stator, wherein the stator includes a plurality of windings and cooling channels arranged to provide cooling to the plurality of windings, a drive unit configured to drive operation of the motor unit, and a cooling system. The cooling system includes an oscillating heat pipe containing a first working fluid, wherein the oscillating heat pipe is arranged to pick up heat from at least one winding, the oscillating heat pipe having an evaporator section arranged in thermal contact with the at least one winding and a condenser section arranged away from the evaporator section and a heat pickup portion arranged to receive a second working fluid to remove heat from the condenser section of the oscillating heat pipe.

Aircraft electric motor having a stator heat pipe cooling scheme

Aircraft electric motors are described. The aircraft electric motors includes a motor unit having a rotor and a stator, wherein the stator includes a plurality of windings and cooling channels arranged to provide cooling to the plurality of windings, a drive unit configured to drive operation of the motor unit, and a cooling system. The cooling system includes at least one cooling channel integrally formed within at least one winding, wherein the at least one cooling channel comprises an inlet to receive a two-phase cooling fluid and an outlet configured to discharge the two-phase cooling fluid, wherein a cross-sectional area of the at least one cooling channel at the inlet is less than a cross-sectional area of the at least one cooling channel at the outlet.

Aircraft electric motor

Growing community of inventors

Amston, CT, United States of America

Joseph E Turney