Hamilton Sundstrand Corporation

Carrier Corporation

Otis Elevator Company

Raytheon Technologies Corporation

Rtx Corporation

Rosemount Aerospace Limited

Simmonds Precision Products, Inc.

Otis Elevatro Company

Jagadeesh Kumar Tangudu

Andrzej Ernest Kuczek

Wayde R Schmidt

Richard Andrew Himmelmann

Vishnu Mohan Sishtla

Richard N Fargo

Abbas A Alahyari

Kimberly Rae Saviers

Joseph E Turney

Parag M Kshirsagar

Thomas M Yun

Beata I Wawrzyniak

Andrew S Babel

Enrico Manes

Aritra Sur

Zaffir A Chaudhry

Wenping Zhao

John A Sharon

James Thompson Beals

Tahany Ibrahim El-Wardany

William A Veronesi

Zbigniew Piech

Ram Ranjan

Walter Thomas Schmidt

Shihemn Chen

Vladimir Blasko

Michael A Klecka

Huan Zhang

Rolando Burgos

Joseph Kenneth Coldwate

Vijay Narayan Jagdale

Suman Dwari

Dmytro Mykolayovych Voytovych

Matthew E Lynch

Sreenivasa R Voleti

Peter Cocks

Tod Policandriotes

Jeffrey P King

Zhentao Stephen Du

Boran Fan

Dong Dong

Kimberly R Saviers

A rotor is provided. The rotor includes a central hub, an outer ring assembly and back-to-back curved webs. The outer ring assembly includes magnetic elements. The back-to-back curved webs are_radially interposed between the central hub and the outer ring assembly. The back-to-back curved webs can be circumferentially continuous about the central hub or circumferentially non-continuous about the central hub.

Lightweight rotor design with composite structure

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

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

A stator for an electrical machine can include a plurality of windings, each forming a coil and end connections. The stator can include a first potting material having a first viscosity and a first thermal conductivity. The first potting material can be disposed on each coil and fills gaps between each coil. The stator can include a second potting material different from the first potting material and having a second viscosity and a second thermal conductivity. The second viscosity can be higher than the first viscosity and the second thermal conductivity is higher than the first thermal conductivity. The second potting material can be disposed on each of the end connections to provide increased thermal conductivity from the end connections.

Multiple potting material structures

Aircraft electric motors include a rotor having magnet segments arranged on a frame of the rotor, the rotor defining an internal cavity radially inward from the magnet segments. An output shaft is operably coupled to the rotor and a stator, having a yoke and at least one winding wrapped about stator teeth, is arranged within the internal cavity of the rotor. The stator defines a radial span as a distance from the yoke to a radial outward edge of the at least one winding. The plurality of stator teeth have at least one tooth formed from a magnetic material with the tooth having an engagement end configured to engaged with the yoke, a distal end opposite the engagement end, and a shaped end at the distal end of the tooth, with a portion of the tooth at the shaped end being closer to the yoke than the radial span.

Aircraft electric motor

A multi-three-phase motor drive system includes a power distribution network, a motor drive unit, and a motor network. The power distribution network includes a partitioned direct current (DC) link connected between a positive voltage rail and a negative voltage rail. A connection between the positive voltage rail and a mid-point node defines an upper portion of the partitioned DC link and a connection between negative voltage rail and the mid-point node defines a lower portion of the partitioned DC link. The motor drive unit includes a plurality of inverter units, and the motor network includes a plurality of motor windings which are each connected to a respective inverter unit. A first group of the inverter units is connected in parallel with the upper portion of the portioned DC link, and a second group of the inverter units is connected in parallel with the lower portion of the partitioned DC link.

Multi-three-phase drive system

Aircraft electric motors include a rotor comprising a plurality of magnet segments arranged on a frame of the rotor, the rotor defining an internal cavity radially inward from the plurality of magnet segments, an output shaft operably coupled to the rotor, a stator comprising at least one winding wrapped about a support structure, the stator arranged within the internal cavity of the rotor, and a stator support configured to supply at least a current into the at least one winding, wherein the support structure is structurally supported on the stator support. The magnet segments are symmetrically arranged about the stator to balance axial forces applied to the rotor when a current is induced within the at least one winding and maintain a gap between the plurality of magnet segments and the at least one winding.

A method for manufacturing a stator for an electric machine comprises manufacturing a slot cooling fin to extend into a slot defined between a first tooth, a second tooth, and a stator yoke, and disposing a coil in the slot, wherein the slot cooling fin extends into the first coil.

Slot cooling fins in electrical machines

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.

An electric motor is provided and includes a U-shaped rotor including circumferentially arranged U-shaped magnets, each circumferentially arranged U-shaped magnet defining an interior, and a stator supportive of a winding structure. The winding structure includes phase coils extending axially and radially within the interior for torque production with each circumferentially arranged U-shaped magnet and end windings respectively extending outside the interior between corresponding ends of sequential pairs of the phase coils.

Electric motor with simplified winding and U-shaped rotor

Aircraft electric motors include a motor unit having a rotor and a stator. The stator includes a plurality of windings and cooling channels arranged to provide cooling thereto. A drive unit is configured to drive operation of the motor unit. A cooling system includes a working fluid arranged within a cooling fluid flow path, wherein the cooling fluid flow path includes a liquid cooling path configured to direct flow of the working fluid through, at least, the cooling channels of the motor unit and a vapor cooling path configured to direct flow of the working fluid through the drive unit and a separator arranged upstream of each of the liquid cooling path and the vapor cooling path and configured to direct a liquid portion of the working fluid into the liquid cooling path and configured to direct a vapor portion of the working fluid into the vapor cooling path.

Aircraft electric motor with integrated cooling system

A stator of an electric motor includes a stator core including a rim and a plurality of stator teeth extending from the rim. The plurality of stator teeth define a plurality of tooth gaps between circumferentially adjacent stator teeth. A plurality of stator windings are wrapped along the plurality of stator teeth. The plurality of stator windings include a plurality of core segments extending along the plurality of tooth gaps, and a plurality of end turn segments connecting adjacent core segments. A plurality of non-electrically conductive cooling channels are located in the stator core. The plurality of cooling channels are configured to direct a cooling fluid flow therethrough to cool the plurality of stator windings.

Electric motor with cooling channels

Aircraft electric motors are described. The electric motors include an annular rotor sleeve having an inner wall, a connecting wall, and an outer wall, wherein the inner wall, the connecting wall, and the outer wall define a U-shaped channel configured to receive a U-shaped magnet structure and a sleeve inner cavity defined radially inward from the inner wall, a hub connector extending radially inward from the inner wall into the sleeve inner cavity, a hub arranged in the sleeve inner cavity and fixedly connected to the hub connector, wherein the hub is configured to rotate with rotation of the rotor sleeve, and a U-shaped magnet structure arranged within the U-shaped channel of the rotor sleeve. At least one of the rotor sleeve, the hub connector, and the hub are formed from a composite material.

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 having at least one directional feature forming a portion of at least one cooling channel, the at least one directional feature configured to prevent backflow of a cooling fluid that passes through the at least one cooling channel.

Growing community of inventors

South Windsor, CT, United States of America

Jagadeesh Kumar Tangudu