United Technologies Corporation

Raytheon Technologies Corporation

Hamilton Sundstrand Corporation

Rtx Corporation

Geoffrey T Blackwell

William J McVey

William G Tempelman

Joseph V Mantese

Coy Bruce Wood

Jonathan Gilson

Richard A Poisson

Goran Djuknic

Gurkan Gok

Martin Richard Amari

James A Gosse

Eric J Heims

Edward John Marotta

Daniel Bernard Kupratis

Steven A Avritch

Gary M McBrien

Bhalchandra R Tulpule

James K Berry

Xiao D He

Andrew M MacKay

An engine ignition system can include a multifunction controller, and an exciter operatively connected to the multifunction controller. The multifunction controller can be configured to control the exciter to output an ignition voltage. The multifunction controller can be configured to perform at least one other engine control function.

Engine ignition systems

Apparatus and associated methods are disclosed that relate to detecting a shaft condition of a gas turbofan engine. Shaft condition is detected based on sensed rotation rates of the shaft at different shaft locations. If the sensed rotations rates of the shaft at the two different shaft locations are indicative of a compromised shaft, such as, for example, a shaft that has sheared, then a fuel cut-off signal is generated. The fuel cut-off signal is then sent to a fuel cut-off valve so as to cut off the fuel supplied to the gas turbofan engine. In some embodiments, shaft condition is determined based on a difference between scaled rotation rates of the shaft at two different shaft locations.

Detecting condition of a shaft of a gas turbofan aircraft engine

A system for bleeding air from a core flow path of a gas turbine engine includes a bleed valve in a bleed air duct configured to receive bleed air from a first entrance point to the core flow path into the bleed air duct; a pressurized air valve in a pressurized air duct configured to receive pressurized air from a second entrance point to the core flow path, the pressurized air at a pressure greater than that received into the first entrance point; an eductor outlet from the pressurized air duct located in the bleed air duct; and a control system operable to control operation of the bleed valve and the pressurized air valve.

Assisted engine start bleed system

A radio frequency waveguide communication system includes a guided electromagnetic transmission network, and a cooling air source. The guided electromagnetic transmission network includes one or more remote node in fluid communication with one or more waveguides. The cooling air source is in fluid communication with the guided electromagnetic transmission network and is configured to provide pressurized cooling air to the waveguide. The waveguides direct the pressurized cooling air to the remote node.

Radio frequency waveguide system including control remote node thermal cooling

A system of a machine includes a network of a plurality of nodes distributed throughout the machine. Each of the nodes is operable to communicate through one or more radio frequencies, where the machine includes a cooler portion and a hotter portion. The system includes a means for communicating with the network of nodes using a higher frequency to communicate with one or more of the nodes in the cooler portion of the machine and a lower frequency to communicate with one or more of the nodes in the hotter portion of the machine.

Radio frequency waveguide system for mixed temperature environments

A method of managing a gas turbine engine includes the steps of detecting an airspeed and detecting a fan speed. A parameter relationship is referenced related to a desired variable area fan nozzle position based upon at least airspeed and fan speed. The detected airspeed and detected fan speed is compared to the parameter relationship to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted in response to the determination of the target area fan nozzle position and at least one threshold.

Gas turbine engine variable area fan nozzle control

A system of a machine includes a network of a plurality of nodes distributed throughout the machine, a controller, and a plurality of waveguides. Each of the nodes is operable to communicate through one or more radio frequencies, where the machine includes a cooler portion and a hotter portion. The controller is operable to communicate with the network of nodes using a higher frequency to communicate with one or more of the nodes in the cooler portion of the machine and a lower frequency to communicate with one or more of the nodes in the hotter portion of the machine. The waveguides are configured to guide transmission of the one or more radio frequencies between the controller and one or more of the nodes.

A method of managing over-temperature excursions in an electronic control unit of a control system having failed-fixed capability and an operationally independent temperature monitoring and power enable function. The method includes receiving a temperature signal indicative of a temperature associated with an electronic control unit, determining if the temperature associated with the electronic control unit exceeds a first selected threshold, determining if the temperature associated with the electronic control unit exceeds a second selected threshold, and ascertaining if an engine associated with the control system is operational. The method also includes that if the engine is not operational and the temperature exceeds the first selected threshold, then disabling an actuator associated with the control system. In addition, the method also includes that if the temperature associated with the electronic control unit exceeds the second selected threshold, then disabling an actuator associated with the control system.

Method for managing over-temperature excursions in a failed-fixed control system

A method of managing a gas turbine engine variable area fan nozzle includes the steps of operating a variable area fan nozzle according to a first operating schedule. An icing condition input is evaluated to determine the likelihood of ice presence. The first operating schedule is altered to provide a variable area fan nozzle position if ice is likely present or actually present to provide an icing operating schedule different than the first operating schedule. The first operating schedule corresponds to the flaps at least partially open at air speeds below a first airspeed. The altering step includes closing the flaps below the first airspeed as part of the icing operating schedule. The variable area fan nozzle position is adjusted according to the icing operating schedule. A fan is arranged in a fan nacelle that includes a flap configured to be movable between first and second positions. An actuator is operatively coupled to the flap.

Gas turbine engine variable area fan nozzle with ice management

A multi-actuation system includes a first electrohydraulic servo valve and a first actuator. A first fluid line fluidically connects the first electrohydraulic servo valve to the first actuator. The multi-actuation system also includes a second electrohydraulic servo valve and a second actuator. A second fluid line fluidically connects the second electrohydraulic servo valve to the second actuator. A ring fluidically connects the first fluid line with the second fluid line.

Multi-actuation control system with pressure balancing plumbing

A method of managing a gas turbine engine variable area fan nozzle includes the steps of evaluating an icing condition to determine the likelihood of ice presence. A variable area fan nozzle position is altered if ice is likely present or actually present. The gas turbine engine includes a fan nacelle including a flap configured to be moveable between first and second positions. An actuator is operatively coupled to the flap. A controller is configured to evaluate an icing condition to determine the likelihood of ice presence. The controller is configured to alter a variable area fan nozzle position schedule if ice is likely present by providing a command to the actuator to adjust the flap from the first position to the second position.

A method of managing a gas turbine engine operating line includes detecting an air speed and a fan speed. A data table is referenced that includes a desired variable area fan nozzle position based upon air speed and fan speed. The detected air speed and detected fan speed are compared to the data table to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted to the target variable area fan nozzle position.

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Vernon, CT, United States of America

Geoffrey T Blackwell