A bowed rotor start mitigation system for a gas turbine engine of an aircraft is provided. The bowed rotor start mitigation system includes a motoring system and a controller coupled to the motoring system and an aircraft communication bus. The controller is configured to determine at least one inferred engine operating thermal parameter based on at least one aircraft-based parameter received on the aircraft communication bus, where the at least one inferred engine operating thermal parameter is based on data describing a history of the aircraft before an engine shutdown. The motoring system is controlled to drive rotation of a starting spool of the gas turbine engine below an engine idle speed based on determining that the at least one inferred engine operating thermal parameter is within a preselected range.

A turbine pump assembly has a turbine, a centrifugal pump, a passive electrical speed control system, and a pneumatic circuit breaker. The pneumatic circuit breaker has a plurality of elements that are configured to move to a position blocking an outlet duct of the turbine when a flow velocity exceeds a predetermined threshold. A rocket thrust vector control system is also disclosed.

Over-acceleration protection mechanism for ICE or turbine speed regulator with a bushing driven by the gears. The bushing, the component, the washer, the thread, are joined together. The component screws to the thread through the thread. The weights are fitted to the component through the pins and the safety clips, including the valve which is secured by the nut. The lid is screwed to the bushing by means of the screws, while the counterweights come out of the openings of the lid. The thrust bearing and the pressure spring are mounted on the component, adjusted by the screw. The device operates through the centrifugal force which forces the counterweights to rotate in its direction of rotation and to displace the valve by compressing the spring. Then the holes of the fittings communicate with each other, allowing the oil to pass through the joints and the tube and actuate the system.

A system and method for adaptively controlling a cooldown cycle of an auxiliary power unit (APU) that is operating and rotating at a rotational speed includes reducing the rotational speed of the APU to a predetermined cooldown speed magnitude that ensures combustor inlet temperature has reached a predetermined temperature value, determining, based on one or more of operational parameters of the APU, when a lean blowout of the APU is either imminent or has occurred, and when a lean blowout is imminent or has occurred, varying one or more parameters associated with the shutdown/cooldown cycle.

A rotational position of a variable-vane of a variable-vane turbine nozzle upstream of a turbine of a gas-turbine engine is biased towards a corresponding rotational position that will mitigate against an overspeed condition of the turbine during operation of the gas-turbine engine. When the turbine is operating at a rotational speed that is less than an overspeed threshold, the rotational position of the variable-vane is controlled independently of the biasing using a variable-vane actuator operatively coupled to the variable-vane. Responsive to a rotational speed of the turbine in excess of the overspeed threshold, the variable-vane actuator is operatively decoupled from the variable-vane so as to provide for the variable-vane to be repositioned towards the corresponding rotational position that will mitigate against the overspeed condition.

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.

A control system for a gas turbine engine is disclosed. In embodiments, control system includes a controller and a high speed recorder. The controller obtains a sensor value from a sensor connected to the gas turbine engine and publishes a tag that includes the type of event, the sensor value, and a timestamp. The high speed recorder checks the tag for an overspeed event. If an overspeed event is detected, the high speed recorder records values provided by the tag.

A control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4), is provided with: a control unit (12) to control a forward operating mode or a reverse operating mode of the gas turbine engine (1); and a supervising unit (14), operatively coupled to the control unit (12), to receive an input signal (PLA) indicative of a forward, or reverse, power request and to cause the control unit (12) to control the forward, or reverse, operating mode based on the input signal (PLA). The supervising unit (14) has an enabling stage (20) to enable a transition between the forward and reverse operating modes based on a check that a safety condition is satisfied.

A turbocharger includes a wastegate valve, an actuator for the wastegate valve, and a link mechanism linking the wastegate valve with the actuator via a specific rod. A plate is a component of the link mechanism and connects the wastegate valve with the rod or connects the rod with the actuator. The plate includes a body portion in a plate shape and a pin portion protruding from the main body portion. The pin portion is in a tubular shape having a hollow portion opened to its outside. The pin portion is engageable with an other component of the link mechanism on its outer periphery to form a rotation axis of the other component.

A control system for limiting power turbine torque (QPT) of a gas turbine engine includes a controller including a processor and memory configured to control the gas turbine engine, the controller including an engine control module that provides an effector command signal to a gas generator of the gas turbine engine; a power turbine governor module that outputs a preliminary torque request (QPT_req_pre); and a power turbine torque (QPT) optimal limiter module that outputs a maximum torque topper (QPT_max) to limit a power turbine speed overshoot of the gas turbine engine; wherein the controller outputs a minimum value between the preliminary torque request (QPT_req_pre) and the maximum torque topper (QPT_max) to the engine control module.