Sikorsky Aircraft Corporation

United Technologies Corporation

Carrier Corporation

Raytheon Technologies Corporation

Rtx Corporation

Otis Elevator Company

Goodrich Corporation

Hamilton Sundstrand Corporation

Utc Fire and Security Corporation

Chubb International Holdings Limited

Johnson and Johnson Vision Care, Inc.

Xinetics, Inc.

Chubb International Holding Limited

Claverham Limited

Zaffir A Chaudhry

Fanping Sun

Ulf J Jonsson

Wenping Zhao

Andrzej Ernest Kuczek

David L Lincoln

Gregory S Hagen

Huan Zhang

Yan Chen

David M Rockwell

Mark W Davis

Scott Goyette

Janet Shaw

Jeffrey P King

Vishnu Mohan Sishtla

Galdemir Cezar Botura

Brian Ernest Wake

Enrico Manes

Walter Thomas Schmidt

Paul Attridge

Tommy Maurice Wilson, Jr

Brad Hartzler

Alan Matthew Finn

Susanne Marie Opalka

Muhidin A Lelic

Michael M Joly

Jagadeesh Kumar Tangudu

Robert H Dold

John M Milton-Benoit

Dilip Prasad

Simon W Evans

Xiaodong Luo

Danbing Seto

Amit Vaidya

Avinash Sarlashkar, Jr

Yifan Qiu

Michael G McCaffrey

Jin Hu

Hongcheng Wang

Xia Tang

Richard J Ericson

Daniel L Gysling

Ying She

Mark R Jaworowski

Zissis A Dardas

Changsheng Guo

Ziyou Xiong

Bruce P Swaybill

Om Parkash Sharma

Nasr A Shuaib

James A Mullen

Daniel G Goberman

Claude G Matalanis

David D Pearson

Loi Cheng

Lee A Hoffman

Gorazd Medic

Jeremiah C Lee

Shihemn Chen

Jeffrey H Roffman

John P Wesson

Abbas A Alahyari

James R Dunphy

Daniel A Mosher

Joel H Wagner

Robin Mihekun Miller

Derick S Balsiger

Goran Djuknic

Vijaya Ramaraju Lakamraju

Robert G Dunster

Paul R Brewer

Nicholas Charles Soldner

Sanjay Bajekal

Mark Steven Thompson

Allan J Volponi

Joshua David Isom

Kimberly Rae Saviers

Ashok K Jain

Thomas Gregory Tillman

Paul R Braunwart

Sheridon Everette Haye

Gregory J Hofmann

Larry G Jones

Charbel Rahhal

Joseph V Paturzo

Richard A Lomenzo

Nicholas R Van De Veire

Scott M MacBain

Thomas A Wynosky

Adam J Ditzler

Andrew John Collins

Aritra Sur

David R Polak

Mark A Ealey

Patrick Louis Clavette

Constantino V Loffredo

Robert H Luppold

Charles C Coffin

John L Kettle

Jeremy Wallet-Laily

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

An in-situ system for a gas turbine engine blade inspection including a sensor system configured to capture images of a forward surface of at least one gas turbine engine blade; a processor coupled to the sensor system, the processor configured to determine damage to the at least one gas turbine engine blade based on video analytics; and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored therein that, in response to execution by the processor, cause the processor to perform operations comprising receiving, by the processor, data for the forward surface of at least one gas turbine engine blade from the sensor system; determining, by the processor, a rotational speed of a fan; and determining, by the processor, a fan synchronization.

Optical in-situ inspection system

An assembly for an aircraft propulsion system includes a propulsor and an imaging assembly. The propulsor includes a propulsor disk, a plurality of propulsor blades, and a nose cone. The plurality of propulsor blades are circumferentially distributed about the propulsor disk. Each propulsor blade of the plurality of propulsor blades extends radially between and to a root end and a tip end. The root end is disposed at the propulsor disk. The propulsor disk and the plurality of propulsor blades are configured to rotate about the rotational axis. The nose cone is disposed axially adjacent the propulsor disk. The imaging assembly includes an imaging device disposed on the nose cone. The imaging device includes a camera. The camera is configured to capture image data of each propulsor blade of the plurality of propulsor blades as the plurality of propulsor blades rotate about the rotational axis.

Propulsor blade imaging assembly method for an aircraft propulsion system

Disclosed is a direct-drive refrigerant screw compressor, having: a housing; a compression chamber in the housing; a pair of rotors, each rotor of the pair of rotors being rotationally disposed in the compression chamber and including an outer surface with a screw-geared profile; a fluid being disposed in the compression chamber, the fluid consisting of a working fluid for providing lubrication to each rotor; a first port extending through the housing and configured for directing the fluid toward the compression chamber; and when the compressor is activated, each rotor rotates and the fluid is distributed about each rotor to lubricate each rotor.

Direct drive refrigerant screw compressor with refrigerant lubricated rotors

An assembly for an aircraft propulsion system includes a propulsor section, an imaging device, a plurality of light sources, and a controller. The propulsor section includes a propulsor. The propulsor includes a plurality of propulsor blades. The imaging device is disposed in the propulsor section. The imaging device includes a camera. The plurality of light sources are disposed in the propulsor section. The controller includes a processor in communication with a non-transitory memory storing instructions, which instructions when executed by the processor, cause the processor to: control the plurality of light sources to direct light to the plurality of propulsor blades, control the camera to capture image data of each propulsor blade of the plurality of propulsor blades, and identify a presence or an absence of damage for each propulsor blade of the plurality of propulsor blades using the image data.

Propulsor blade imaging assembly for an aircraft propulsion system

An assembly for an aircraft propulsion system includes a propulsor section and an imaging device. The propulsor section includes a propulsor and a structural body. The propulsor includes a plurality of propulsor blades. The structural body forms an outer air flow surface forming a portion of an air flow path through the propulsor section. The imaging device includes a housing and a camera. The housing includes a housing body and a cover. The housing body is mounted in the structural body. The housing body forms a cavity and an opening of the cavity. The cover is pivotable between a stowed position and a deployed position. The camera is disposed in the cavity with the cover positioned in the stowed position. The camera is configured to capture image data of each propulsor blade of the plurality of propulsor blades with the cover positioned in the deployed position.

An inspection system for rotating fan rotor blades is provided that includes a plurality of cameras and light sources and a system controller. The cameras are controllable to capture an image of a leading edge of a fan rotor blade and produce signals representative of the captured image. Each respective camera is mounted with an inlet guide vane disposed forward of the fan rotor blade stage. The light sources are each associated with a respective camera. The system controller is in communication with the cameras, the light sources, and a non-transitory memory storing instructions. The instructions when executed cause the system controller to: control the light sources to selectively illuminate the fan rotor blades, and control the cameras to image respective fan rotor blades and produce signals representative thereof, and provide inspection information representative of the leading edge of respective fan rotor blades.

Rotor blade inspection system

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

An inspection system for fan rotor blades in a gas turbine engine is provided. The gas turbine engine has a sensor that provides a fan rotor stage speed signal. The system includes a plurality of cameras and light sources and a system controller. The cameras are controllable to image a leading edge of a fan rotor blade. Each respective camera and light source is mounted with a static structure disposed forward of the fan rotor blade stage. The system controller is in communication with stored instructions that when executed cause the system controller to monitor the speed of the fan rotor stage during an engine shutdown; upon the fan rotor stage speed reaching a first value, control the light sources to selectively illuminate the fan rotor blades, and control the cameras to image the fan rotor blades, and provide inspection information using signals representative of the captured images.

An inspection system for rotating fan rotor blades in a gas turbine engine is provided. The system includes a plurality of cameras and lids, and a cleaning system. The cameras are each controllable to capture an image of a leading edge of a fan rotor blade and produce signals representative thereof. Each camera is mounted to a static structure disposed forward of the fan rotor blade stage. The lids are attached to the static structure and is selectively movable between closed and open positions. In the closed position at least one camera is enclosed. In the open position the camera is at least partially exposed and has a field of view of the rotating fan rotor blades. The cleaning system is controllable to selectively produce a body of fluid relative to the at least one camera when the respective lid is in the open position.

A refrigeration system includes a compressor for compressing a refrigerant, a condenser for cooling the refrigerant, an evaporator for heating the refrigerant, and a lubrication system for providing a lubricant mist to a movable component of the compressor. The lubrication system includes an ejector arranged in fluid communication with the compressor and the evaporator, wherein the lubricant mist is carried by the refrigerant to the movable component.

Enhanced method of lubrication for refrigeration compressors

Aircraft electric motors are described. The aircraft electric motors include a cooling system comprising an annular heat exchanger, a motor housing arranged radially inward from the heat exchanger, the motor housing defining a rotor-stator cavity and a gear assembly cavity, a rotor sleeve arranged within the rotor-stator cavity, a gear assembly arranged within the gear assembly cavity, a first shaft operably coupled to the rotor sleeve and configured to be rotationally driven by the rotor sleeve to drive rotation of a portion of the gear assembly, and a second shaft operably coupled to the gear assembly and configured to be rotationally driven by the gear assembly.

Aircraft electric motor

A gas turbine engine includes a fan section, a compressor section, and a turbine section. The fan section has a plurality of vane assemblies spaced circumferentially about an engine axis. The vane assemblies each include an airfoil extending between a leading edge and a trailing edge, a control rod extending through the airfoil, and a mechanism driven by the control rod to change the shape of the airfoil. A vane system for a gas turbine engine is also disclosed.

Growing community of inventors

South Glastonbury, CT, United States of America

Zaffir A Chaudhry