Rolls-royce Corporation

Rolls-royce North American Technologies Inc.

Rolls-royce Singapore Pte. Ltd.

Rolls-royce Electrical Norway As

Rolls-royce Corporation/rolls-royce Singapore Pte. Ltd.

David Russell Trawick

Chandana Jayampathi Gajanayake

David Loder

Shuai Wang

Mathew Hill

Roar Furuhaug

Daniel Lawrence Phelps

Erlend Engevik

Eirik Mathias Husum

Stephen Andrew Long

Peter Michael Schenk

Sean Andrew Morgan

Souvik Dasgupta

John Timothy Alt

Suvajit Mukherjee

Shaui Wang

Kolbeinn Kristjansson

Matthew Hill

Sara Jocelyn Abruzzo

An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide vertical propulsion of the aircraft and a respective electrical machine of a plurality of electrical machines, each respective electrical machine configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

Hybrid propulsion systems with power sharing

An example aircraft includes a parallel propulsion unit, the parallel propulsion unit comprising: a propulsor configured to provide forward propulsion of the aircraft; a gas turbine engine configured to drive the propulsor; an electrical machine configured to generate, for output via one or more electrical busses, electrical energy using mechanical energy derived from the gas turbine engine; and a power sharing module configured to control a ratio of the mechanical energy derived from the gas turbine engine used to drive the propulsor and used to generate electrical energy; and a plurality of series propulsion units, each series propulsion unit comprising a respective propulsor of a plurality of propulsors that are configured to provide forward propulsion of the aircraft and a respective electrical machine each configured to drive a respective propulsor of the plurality of propulsors using electrical energy received from one or more electrical busses.

An example electrical machine is described that includes active segments for variable voltage generation. The electrical machine includes a drive shaft, a fixed rotor segment, an active rotor segment, and an actuator mechanism. The fixed rotor segment is coupled to the drive shaft, where the fixed rotor segment has affixed thereon first permanent magnets of alternating polarity. The active rotor segment axially is adjacent to the fixed rotor segment along the drive shaft. The active rotor segment also has affixed thereon second permanent magnets of alternating polarity. The actuator mechanism is configured to articulate the active rotor segment relative to the fixed rotor segment and thereby alter a phase of the second permanent magnets relative to the first permanent magnets in order to change a first voltage generated by the electrical machine to a second voltage generated by the electrical machine.

Electrical energy system having active segments for variable voltage generation

An aircraft includes an internal combustion engine and an electrical power system. The electrical power system includes a permanent magnet machine and an inverter coupled to the permanent magnet machine. The permanent magnet machine includes a stator and a rotor configured to rotate relative to the stator.

Aircraft with engine-driven permanent magnet generator

An aircraft includes an engine and an electric power system. The electric power system includes a permanent magnet machine. The permanent magnet machine includes a stator and a rotor configured to rotate relative to the stator.

Systems and methods for intentionally breaking shafts of compromised electric machines with electro-thermal activation

A turbo-generator system for generating propulsive electrical power for an aircraft includes an electric machine comprising: a rotor configured to be rotated by a gas-turbine of the turbo-generator system; a stator comprising: a first active section comprising first windings surrounding a first portion of the rotor, and a second active section comprising second windings surrounding a second portion of the rotor.

Fault tolerant turbo-generator system

An example system comprises an electric machine including a stator and a rotor, a cooling system configured to supply a cooling fluid to cool the electric machine, and a stator tube configured to contain the cooling fluid within a stator portion of the electric machine and prevent the cooling fluid from contacting the rotor.

Electric machine cooling of stator with tube

A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.

Voltage controlled aircraft electric propulsion system

An electrical assembly, such as a multi-layer bus bar, includes an electrical connection pin and a plurality of electrically conductive layers. Each of the electrically conductive layers is formed to define a cutout therein to receive the electrical connection pin and allow access for joining material to join the electrical connection pin with the plurality of electrically conductive layers. Each of the cutouts is formed to include a first through hole arranged around the electrical connection pin and a second through hole located radially outward of the first through hole.

Multilayer electronic components with soldered through holes

An example system includes an electrical energy storage system (ESS) comprising: an upper node and a lower node; a first set of battery modules that are connected in series; a second set of battery modules that are connected in series; a DC/DC converter electrically in series with the first set of battery modules between the upper node and the lower node, wherein the DC/DC converter sources electrical energy from the second set of battery modules; and a controller configured to adjust an output voltage of the DC/DC converter such that a voltage across the upper node and the lower node is maintained at a specified output voltage level.

Electrically propelled aircraft with partially rated converter

A system includes a first generator configured to output a first plurality of AC signals; a second generator configured to output a second plurality of AC signals; a first set of rectifiers configured to convert the first plurality of AC signals into a first plurality of DC signals for output onto a first DC bus, wherein each of the first set of rectifiers includes a respective contactor configured to de-couple a DC output of the respective rectifier from the first DC electrical bus; and a second set of rectifiers configured to convert the second plurality of AC signals into a second plurality of DC signals for output onto a second DC bus, wherein each of the second set of rectifiers includes a respective contactor configured to de-couple a DC output of the respective rectifier from the second DC bus.

Hybrid aircraft having rectifier with integrated protection

An electrical assembly, such as a multi-layer bus bar, includes an electrical connection pin and a plurality of electrically conductive layers. Each of the electrically conductive layers is formed to define a cutout therein to receive the electrical connection pin and allow access for joining material to join the electrical connection pin with the plurality of electrically conductive layers. Each of the cutouts is formed to include a first portion arranged around the electrical connection pin and a second portion located radially outward of the first portion.

Multilayer copper bus bars with soldered through hole components

An electrically insulated shaft coupling may include a first metallic portion, a second metallic portion, and an electrically insulating portion that separates the first metallic portion and the second metallic portion. The first metallic portion may include a first plurality of splines configured to interface with splines of a first rotating shaft, and the second metallic portion comprises a second plurality of splines configured to interface with splines of a second rotating shaft.

Electrically insulated shaft coupling

An example system includes an electric machine, an alternating current (AC)/direct current (DC) converter, a Y-capacitor, and a controller. The AC/DC converter being connected to the electric machine and having a DC side and an AC side. The Y-capacitor is located on the DC side of the AC/DC converter. The controller is configured to determine, based on a measurement of the DC side of the AC/DC converter, an occurrence of a ground fault on the AC side of the AC/DC converter, and control, based on the occurrence of the ground fault, operation of the AC/DC converter.

Detection and control of motor drive during an AC side ground fault

A cold plate assembly for cooling an electronic device includes a manifold, a comb insert, and a first vaned plate. The manifold is formed to define a cavity therein. The comb insert is located in the cavity includes channels defined by walls for receiving a fluid from passages in the manifold and transferring heat to the fluid. The first vaned plate includes a first panel and first channel vanes extending away from the first panel. The first vaned plate is removably coupled with the comb insert such that first channel vanes are located within the channels to guide the fluid. Each first channel vane extends from a wall toward a neighboring wall at an angle to direct the fluid to impinge upon the neighboring wall with increased velocity so as to increase the heat transfer between the neighboring wall and the fluid.

Growing community of inventors

Indianapolis, IN, United States of America

David Russell Trawick