Hamilton Sundstrand Corporation

Raytheon Technologies Corporation

Rtx Corporation

United Technologies Corporation

Otis Elevator Company

Carrier Corporation

Other

Goodrich Corporation

Sikorsky Aircraft Corporation

Ami Industries, Inc.

Utc Fire and Security Corporation

B/e Aerospace, Inc.

Claverham Limited

United Technologies Research Center

Andrzej Ernest Kuczek

Wayde R Schmidt

Wenping Zhao

Paul F Croteau

Ellen Y Sun

Zaffir A Chaudhry

Tahany Ibrahim El-Wardany

Jagadeesh Kumar Tangudu

John P Wesson

Joseph E Turney

Justin R Hawkes

Abbas A Alahyari

Ulf J Jonsson

Daniel V Viens

Brian St Rock

Ram Ranjan

Kimberly Rae Saviers

Joseph V Mantese

Lawrence A Binek

Parmesh Verma

Charles E Lents

Scott Alan Eastman

Thomas D Radcliff

Om Parkash Sharma

Brian Ernest Wake

Dilip Prasad

Daniel L Gysling

Alan Matthew Finn

Adam Kuenzi

Ying She

Aaron T Nardi

Zissis A Dardas

William A Veronesi

Richard J Ericson

David Ulrich Furrer

Enrico Manes

Matthew Robert Pearson

Wayne F Larson

John E Holowczak

Vijaya Ramaraju Lakamraju

Zhongtao Dai

Vladimir Blasko

Joseph C Rampone

Michael M Joly

Thomas J Garosshen

Huan Zhang

Matthew E Lynch

Subramanyaravi Annapragada

Wei Xie

Thomas M Yun

Simon W Evans

Neal R Herring

Claude G Matalanis

Zhigang Wang

Paul R Faughnan, Jr

John A Sharon

Derick S Balsiger

Michael A Klecka

Thomas J Martin

John D Riehl

Fanping Sun

Matthew S Hill

Paul R Brewer

Yinshan Feng

Gajawalli V Srinivasan

Dmytro Mykolayovych Voytovych

Mikhail B Gorbounov

Peter A T Cocks

James M Draper

Xiaodong Luo

Michael K Ikeda

Randy P Salva

Georgi Kalitzin

Krzysztof Barnat

Robin H Fernandez

Christopher Britton Greene

Aritra Sur

David R Polak

Stuart S Ochs

Patrick Louis Clavette

Robert E Erickson

Jeffrey P King

Shihemn Chen

Eric Hansell

Andrew Smeltz

Lee A Hoffman

Gorazd Medic

Philip Andrew Varney

Aayush Desai

Joseph B Wysocki

Ritesh Khire

Dustin Frame

Yasmin Khakpour

Benjamin Bedard

Joe J Liou

John J Kriss

James M Donohue

Kimberly R Saviers

Duan Liang

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

A composite pressure vessel assembly includes a first and second vessels aligned side-by-side. Each vessel has a liner defining respective chambers. First and second mid-layers of the assembly cover the respective liners with portions of the respective mid-layers being in contact with one-another. An outer layer of the vessel assembly is in contact with and substantially envelops both mid-layers except for the mid-layer portions.

Composite pressure vessel assembly and method of manufacturing

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 method is provided for machining a workpiece. During this machining method, an aperture is formed in the workpiece using a machining system. The machining system includes an ultrasonic machining device, a slurry delivery device and a controller. The forming of the aperture includes delivering a slurry to an interface between the ultrasonic machining device and the workpiece using the slurry delivery device, and transmitting ultrasonic vibrations into the slurry using the ultrasonic machining device. A feedback parameter is monitored during the forming of the aperture using the controller. A slurry delivery parameter for the slurry delivery device is adjusted during the forming of the aperture based on the feedback parameter using the controller.

Ultrasonic machining an aperture in a workpiece

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

In accordance with at least one aspect of this disclosure, a method includes installing a welding tool into a repair tool holder, ultrasonic welding a repair sheet to a part to be repaired with the welding tool, removing the welding tool from the repair tool holder, installing a machining tool into the repair tool holder, and ultrasonic machining a portion of the repair sheet that is welded to the part to be repaired to match an a predetermined geometry of the part to be repaired with the machining tool.

Systems and methods for ultrasonic repair

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

An airfoil for a gas turbine engine including an airfoil body extending between a leading edge and a trailing edge and between a pressure side and a suction side. The airfoil body includes a strut portion extending from the leading edge and a flap portion extending from the trailing edge. The flap portion is pivotable relative to the strut portion. A flexible skin surrounds both the strut portion and the flap portion on both the pressure side and the suction side.

Morphing structures for fan inlet variable vanes

A gear system, having: first and second ground gear; a drive shaft disposed along a rotation axis of the gear system and configured to rotate about the rotation axis; and an output gear supported by the first and second ground gear and configured to rotate by engagement between a wave generator portion of a drive shaft, a wave generator bearing, a flex spline, the output gear and the first and second ground gear, the output gear defining: an output gear body; and first and second output arms respectively extending radially outward from opposite sides of the output gear body to respectively define first and second radial inner ends and radial outer ends of the first and second output arms, so that the first and second radial outer ends are disposed on a radial axis that extends through a radial center of the gear system.

Compound harmonic gear system with dual output arms

A system for deep rolling a fan blade including a shaft assembly disposed along a first axis; a hub connected to a distal end of the shaft assembly, the hub having an upper hub portion and a lower hub portion extending along a second axis, the second axis forming an angle relative to a first axis; a roller disk joined to the lower portion of the hub, the roller disk configured to contact a fan blade; a fixture supporting the fan blade; the fixture comprising a body supporting a pivot clamp attached to the body with a pivot; a support attached to the body, the support is configured to engage an airfoil portion of the fan blade; a receiver formed in the body for supporting a root of the fan blade; and a shoulder attached to the body configured to support a platform portion of the fan blade.

Surface treatment system design for high fatigue life hollow fan blades

An instrumented vane body is provided that includes a suction side and pressure side outer walls, an interior cavity, at least one supply conduit, a plurality of sensors, and a plurality of sensor ports. The suction and pressure side outer walls extend chordwise between leading and trailing edges and between inner and outer radial ends. The supply conduit is in fluid communication with the interior cavity, and is in communication with the interior cavity through at least one of the inner or outer radial ends. The sensor ports are disposed in the leading edge and each is configured to receive a sensor, and are spaced apart from one another. Each sensor port is in fluid communication with at least one vent aperture, and each is configured to permit core gas to enter that sensor part and exit the vane body through the at least one vent aperture.

Gas turbine vane body with instrumentation

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

A heat exchanger includes a body, a plurality of first flow channels defined in the body; and a plurality of second flow channels defined in the body. The second flow channels are fluidly isolated from the first flow channels. The first flow channels and second flow channels are arranged in a checkerboard pattern.

Heat exchangers

A method of manufacturing a composite vessel assembly () includes the steps of filling a first chamber defined by a first liner () with a first granulated material () through a first orifice () in the first liner. A vacuum is then applied to the first chamber, and the first orifice is plugged. The first liner may then be enveloped with a first layer () for structural rigidity followed by relief of the vacuum.

Method of manufacturing a composite vessel assembly

An inlet header having: an inner end, an outer end, a plurality of segments therebetween, including: an outer segment that extends from the outer end to a first intermediate end, the outer segment defines a cylindrical profile; a first intermediate segment that forms an outer elbow and extends from the first intermediate end to a second intermediate end, the second intermediate end has a rectangular shape, and the first intermediate segment increases in width proportionally as it extends toward the second intermediate end; a second intermediate segment that extends from the second intermediate end to a third intermediate end, the third intermediate end has a rectangular shape, and the second intermediate segment increases in width and height proportionally as it extends toward the third intermediate end; and an inner segment that forms an inner elbow and extends from the third intermediate end to the inner end of the inlet header.

Low loss inlet header for fuel cells

Growing community of inventors

Bristol, CT, United States of America

Andrzej Ernest Kuczek