General Electric Company

Ge Medical Systems Global Technology Company, LLC

Michael Solomon Idelchik

Narendra Digamber Joshi

Brian D Lounsberry

Bernard Patrick Bewlay

Ambarish Jayant Kulkarni

Hrishikesh Keshavan

Byron Andrew Pritchard

Guanghua Wang

Mehmet Muhittin Dede

Jonathan Richard Schmidt

Stephen W Gravelle

James S Shepard

Mohamed Ahmed Ali

Douglas J Snyder

Bijan Dorri

Arlie Russell Martin

Louis Robert Nerone

Konrad Roman Weeber

David Joseph Kachmarik

Thomas Gerard Ebben

Michael Charles Ostrowski

Joseph C Oberle

Bharat S Bagepalli

Raymond K Seymour

Kanakasabapathi Subramanian

Douglas Carl Hofer

Seyed Gholamali Saddoughi

Thomas Frederick Papallo, Jr

John William Carbone

Aniruddha Dattatraya Gadre

Kathleen Ann O'Brien

Benjamin Edward Beckmann

Mark A Preston

Matthew Patrick Boespflug

Owen Jannis Schelenz

Vivek Bhatt

David Allen Gutz

Cathleen Ann Hoel

Grover Andrew Bennett

Khan Mohamed Khirullah Genghis Khan

William J Keim

Nicole Christine Reeves Hedges

An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.

Spray nozzle device for delivering a restorative coating through a hole in a case of a turbine engine

A coated component including a slotted ceramic coating with a reactive phase coating disposed thereon for improved resistance to environmental contaminant compositions, along with methods of its formation, is provided. The coated component may include a substrate defining a surface, a ceramic coating disposed on the surface of the substrate, and a reactive phase coating disposed on the layer of environmental contaminant compositions. The ceramic coating includes a plurality of slots disposed in the ceramic coating forming segments of ceramic coating material.

Slotted ceramic coating with a reactive phase coating disposed thereon for improved CMAS resistance and methods of forming the same

A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.

Motor driven propulsor of an aircraft

A propulsion system for an aircraft includes a turbomachine, a primary fan, and an electric machine. The turbomachine includes a first turbine and a second turbine, with at least one of the first turbine or second turbine operably connected to the electric machine and the second turbine driving the primary fan. The propulsion system additionally includes an auxiliary propulsor assembly configured to be mounted at a location away from the turbomachine and the primary fan. The electric machine is in electrical communication with the auxiliary propulsor assembly for transferring power with the auxiliary propulsor assembly during operation of the propulsion system.

Propulsion system for an aircraft

According to some embodiments, a lossless protection procedure may be applied to control distribution of a print geometry of an industrial asset item. For example, an item definition data store may contain electronic records defining a geometry of the industrial asset item. A signature identifier encoder platform may determine a unique signature identifier associated with the industrial asset item and modify the geometry of the industrial asset item to encode therein information about the unique signature identifier. In some cases, for example, this may be done by adjusting a scanning pattern of a fill region (e.g., stripe, checkerboard, etc.) or a support structure of the industrial asset item. An authentication platform may then receive, from a sensor (e.g., an X-ray), a measured characteristic parameter of an item to be authenticated and determine a signature identifier of the item (which can be used to authenticate the item).

System and method to protect items associated with additive manufacturing

An aircraft propulsor assembly includes a fan having a nacelle and plural fan blades radially disposed within the nacelle. The fan blades are configured to be rotated by torque generated by a turbine engine of an aircraft to generate thrust for propelling the aircraft. The assembly also includes an electric motor including a stator in the nacelle of the fan and a rotor in tips of two or more of the fan blades. The electric motor is configured to generate torque that also rotates the fan blades to generate thrust for propelling the aircraft. The assembly also includes a controller configured to reduce or prevent an increase in an operating temperature of the turbine engine of the aircraft by automatically supplanting at least some of the torque generated by the turbine engine with the torque generated by the electric motor.

Propulsor assembly for an aircraft

An atomizing spray nozzle device includes plural inlets that receive different phases of materials of a coating. The device also includes an atomizing zone housing portion fluidly coupled with the inlets and shaped to mix the different phases of the materials into a mixed phase slurry. The device also includes a plenum housing portion fluidly coupled with the atomizing housing portion along the center axis of the device. The plenum housing portion includes an interior plenum that is elongated along the center axis of the device. The plenum is configured to receive the mixed phase slurry from the atomizing zone. The device also includes one or more delivery nozzles fluidly coupled with the plenum. The one or more delivery nozzles provide one or more outlets from which the mixed phase slurry is delivered onto one or more surfaces of a target object as a coating on the target object.

A virtual aerodynamic component for a wind turbine including at least one rotor blade connected to a hub. The at least one rotor blade defines an inner portion and a profiled outer portion. The virtual aerodynamic component includes one or more air-blowing units configured to provide a flow of air substantially opposed to an incoming wind. The flow of air defines the virtual aerodynamic component in front of the inner portion of the at least one rotor blade and provides for redirection of the incoming wind toward the profiled outer portion of the at least one rotor blade in an operational state and allows the incoming wind to flow toward the inner portion of the at least one rotor blade in a non-operational state. Further described is a wind turbine including the above-described virtual aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine.

Apparatus and method for aerodynamic performance enhancement of a wind turbine

A turbine engine assembly is provided. The assembly includes a low-pressure turbine assembly including a first turbine section configured to rotate in a first rotational direction at a first rotational speed, and a second turbine section configured to rotate in a second rotational direction at a second rotational speed. The second rotational direction is opposite the first rotational direction and the second rotational speed is lower than the first rotational speed. The assembly also includes a first drive shaft coupled to the first turbine section, and a fan assembly including a first fan section coupled to the first drive shaft such that the first fan section rotates in the first rotational direction at the first rotational speed, and a second fan section coupled to the second turbine section such that the second fan section rotates in the second rotational direction at the second rotational speed.

Turbine engine assembly and method of manufacturing

A shrouded fan assembly for use with a gas turbine engine includes a central hub and a plurality of variable-pitch fan blades coupled to and extending radially outward from the central hub. Each variable-pitch fan blade includes a radially outer tip is rotatable about a longitudinal axis extending therethrough. A shroud is coupled to each radially outer tip.

Pitch change mechanism for shrouded fan with low fan pressure ratio

A tuned cavity rotating detonation combustion system includes a an annular chamber having an inlet and an outlet; a valve plate at the inlet of the annular chamber and comprising a plurality of openings spaced circumferentially around the inlet; a plurality of tubes each having an open end in communication with a corresponding opening of the valve plate and a closed end forming a tuned cavity, and a first opening between the open end and the closed end for injection of air; and a plurality of fuel injectors corresponding to the plurality of tubes, each fuel injector being configured to inject fuel into the tube between the first opening and the open end. Each of the tuned cavities has a length sized to resonate at a same frequency as a continuous detonation frequency of at least one detonation wave in the annular chamber. Alternately, or additionally, a plurality of flame arresters corresponding to the plurality of tubes are configured to arrest the at least one detonation wave generated in the detonation chamber from travelling into the tube.

Tuned cavity rotating detonation combustion system

A system that includes micro-electromechanical system switching circuitry, such as may be made up of a plurality of micro-electromechanical switches, is provided. The plurality of micro-electromechanical switches may generally operate in a closed switching condition during system operation. A controller is coupled to the electromechanical switching circuitry. The controller may be configured to actuate at least one of the micro-electromechanical switches to a temporary open switching condition while a remainder of micro-electromechanical switches remains in the closed switching condition to conduct a load current and avoid interrupting system operation. The temporary open switching condition of the switch is useful to avoid a tendency of switch contacts to stick to one another.

System and method for avoiding contact stiction in micro-electromechanical system based switch

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Niskayuna, NY, United States of America

Michael Solomon Idelchik