A gas turbine engine for an aircraft that includes a nacelle, a fan, an engine core, a bypass duct extending between the engine core and the nacelle and guiding a bypass airflow through the bypass duct, and at least one non-structural strut extending in the radial direction within the bypass duct, wherein the non-structural strut includes an outside wall acting as a heat exchanger, and wherein the outside wall includes first transport means configured to transport in the outside wall at least one fluid to be cooled. It is provided that the non-structural strut further includes second transport means configured to transport a fluid to be heated, wherein the first transport means and the second transport means are configured such that the fluid to be heated is heated by the at least one fluid to be cooled and the at least one fluid to be cooled is cooled both by the bypass airflow and the fluid to be heated.

The present disclosure relates to methods for starting and rapidly decelerating a turbomachine in a power generation system that utilizes a supercritical fluid in a closed cycle.

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative $\left(\frac{dN2i}{dt}\right)”,$
and automatically stopping the engine when the current derivative $\left(\frac{dN2i}{dt}\right)$
changes sign.

A fan brake system for controlling an industrial fan system, the fan brake system including a fan brake having a brake pad movable on the fan brake to selectively engage the fan system. An actuator including a motor can be operable to cause the fan brake to perform a braking procedure on the fan system to resist rotational movement of the fan system. A controller can be communicated with the actuator, the controller operable to selectively cause the actuator and the fan brake to perform the braking procedure, wherein the controller is operable to monitor and control power being supplied to the motor of the actuator during the braking procedure to maintain a torque output of the motor according to a predetermined torque profile during the braking procedure.

An actuator system for actuating a movable structure of a thrust reverser, the system including a first motor, a first actuator driven by the first motor, a second actuator, and a first transmission shaft that is connected to the second actuator and to the first motor so that the second actuator is driven by the first motor, a second motor, a third actuator driven by the second motor, a fourth actuator, and a second transmission shaft that is connected to the fourth actuator and to the second motor so that the fourth actuator is driven by the second motor, and control means for controlling the motors to cause the first actuator, the second actuator, the third actuator, and the fourth actuator to be driven synchronously by the two motors. The invention also relates to a thrust reverser and to a jet engine fitted with such an actuator system.

At timing t0, a brake gas (raw material gas) starts to be supplied to an ion beam generator, and the brake gas is fed into a turbo molecular pump. After timing t1, a vent valve is opened intermittently to feed atmospheric air into the turbo molecular pump. The brake gas may be different from the raw material gas. The brake gas is supplied using a gas supply system.

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative

[00001]$\left(\frac{dN2i}{dt}\right)”,$

and automatically stopping the engine when the current derivative

[00002]$\left(\frac{dN2i}{dt}\right)$

changes sign.

A fan brake system for controlling an industrial fan system, the fan brake system including a fan brake having a brake pad movable on the fan brake to selectively engage the fan system. An actuator including a motor can be operable to cause the fan brake to perform a braking procedure on the fan system to resist rotational movement of the fan system. A controller can be communicated with the actuator, the controller operable to selectively cause the actuator and the fan brake to perform the braking procedure, wherein the controller is operable to monitor and control power being supplied to the motor of the actuator during the braking procedure to maintain a torque output of the motor according to a predetermined torque profile during the braking procedure.

An assembly is provided for an aircraft propulsion system. This assembly includes a sun gear, a ring gear, a plurality of intermediate gears, a carrier, a first brake and a second brake. The sun gear is rotatable about a centerline axis. The ring gear circumscribes the sun gear and is rotatable about the centerline axis. The intermediate gears are arranged circumferentially about the centerline axis. Each of the intermediate gears is meshed between the sun gear and the ring gear. The carrier is rotatable about the centerline axis. Each of the intermediate gears is rotatably mounted to the carrier. The first brake is configured to slow and/or stop rotation of the ring gear about the centerline axis. The second brake is configured to slow and/or stop rotation of the carrier about the centerline axis.

The invention relates to a structural assembly for a gas turbine engine, which structural assembly comprises a fan and a forked fan shaft, which is coupled to the fan and comprises a radially outer fan shaft and a radially inner fan shaft being fixedly connected to the fan, and the predetermined breaking point being designed to break when a fan blade is lost. A contact mechanism is provided, which is activated by a decrease in the rotational speed of the fan shafts and which couples the radially inner fan shaft to the radially outer fan shaft when the rotational speed of the fan shafts falls below a predefined rotational speed after the predetermined breaking point has broken. After the fan shafts have been coupled by the contact mechanism, radially acting forces are transmitted from the radially inner fan shaft to the radially outer fan shaft.