General Electric Company

Ge Aviation Systems Limited

Thomas William Brown

Paul Robert Gemin

Dominic L Barone

Di Pan

Robert Charles Hon

Gregory Lee Detweiler

Justin Paul Smith

Gerald W Young

Alan Gregory Murphy

Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, and a voltage regulator. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.

Aircraft propulsion system with voltage regulator

An aircraft that includes a hybrid-electric propulsion system is provided. In one aspect, the hybrid-electric propulsion system includes at least one propulsor that includes a gas turbine engine and an electric machine mechanically coupled with a spool of the gas turbine engine. When idle operation is commanded, electrical power is provided to the electric machine to cause the electric machine to apply torque to the spool and fuel provided to the engine can be reduced. Thus, the electric machine is controlled to provide a power assist to maintain the engine at the commanded idle speed whilst reducing fuel consumption.

Electric machine power assist of turbine engine during idle operation

A system for controlling a motor includes a controller module comprising a controller portion, a regulator portion and an integrator portion. The regulator portion includes a set of regulator modules communicatively coupled in a sequence. Each regulator module configured to receive a respective input signal, indicative of a target or selected value, from the controller portion or the immediately preceding regulator module in the sequence, determine a respective selectable value; select one of the respective selectable value and the value indicated by the received input signal; and provide the selected value as an output signal to the next regulator module in the sequence or the integrator module. The integrator module is configured to receive the output signal from the last regulator module in the sequence, calculate a final demand value based on the received signal, and provide an output signal indicative of the final demand value.

Method and apparatus for controlling a motor

Aspects of the disclosure generally relate to an aircraft propulsion system for an aircraft. The aircraft propulsion system can include at least an electric power source, an electric machine, a voltage regulator, and at least one propeller. The voltage regulator regulates the electrical power provided to the electric machine from the electrical power source. The electric power source is capable of providing an AC or DC electrical output and can include a combustion engine with a generator or an electrical storage device.

A multi-spool turbomachine having an electric machine that can be controlled to input power to one of the spools of the turbomachine is provided. In one aspect, the multi-spool turbomachine can be a hybrid electric gas turbine engine for an aircraft. The hybrid electric gas turbine engine can include a first spool, a second spool, and an electric machine operatively coupled with the first spool. In response to an increase in thrust demand, the electric motor receives electrical power from an electrical power source. In turn, the electric machine applies a torque to the first spool, causing the first spool to increase in rotational speed. In this manner, the electric machine can electrically assist the turbomachine to meet the increase in thrust demand.

Electric machine assistance for multi-spool turbomachine operation and control

Methods for detecting events, e.g., failures, in actuating systems for turbine engines are provided. In one exemplary aspect, a first slope and a second slope are determined. The first slope is determined by calculating the slope of an engine operating characteristic as a function of time prior to an actuation command. The second slope is determined by calculating the slope of the engine operating characteristic as a function of time after the actuation command. Thereafter, a delta slope is generated based at least in part on the difference between the first slope and the second slope. The delta slope is then compared to a predetermined threshold to determine whether a failure in the actuating system has occurred. Turbine engines configured to detect such events are also provided.

Slope-based event detection for turbine engines

This separable electrical connector module, which is movable through an operating stroke and is adapted to couple with a mating module, comprises: (a) a connector member including a copper portion containing a hole having a central longitudinal axis and internal threads surrounding the axis, and (b) a copper contact rod having one end that is externally threaded to provide external threads that mate with said internal threads and an opposite end adapted to engage a contact within the mating module. The external threads are restrained against rotation with respect to the mating internal threads by means comprising: (a) a passage in the connector member portion that intersects said internal threads in a predetermined location at one side of the central axis, and (b) a pin of plastic material tightly fitting within said passage and bearing against the external threads of the contact rod to provide a radial force on the contact rod that urges the external threads of the contact rod into high pressure engagement with the internal threads at the opposite side of the longitudinal axis from said predetermined location, thus maintaining a good electrical connection between the threads of the contact rod and the connector member despite repeated motion of the module through its operation stroke.

Separable connector module with improved current-carrying threaded joint

An electrical circuit adapted to control the operation of a refrigerant compressor in an automotive type air conditioning system. The electrical circuit has a pair of branch circuits, an impedance for connection in the branch circuits so as to be respectively energized and shunted therein, and condition responsive devices for enabling and disenabling one of the branch circuits. Switching means is operable for sequentially energizing and then shunting the impedance in the branch circuits to control the energization thereof subject to the enablement and disenablement of the one circuit branch by the condition responsive device. A method of operating an electrical circuit to control the operation of a refrigerant compressor in an automotive type air conditioning system is also disclosed.

Growing community of inventors

Cincinnati, OH, United States of America

Thomas William Brown