Oil transfer tube for a system to control the regulation of a turbine engine propeller pitch, in particular of an aircraft, the tube being intended to be mounted coaxially inside a tubular shaft of the propeller, the tube having an elongated shape and including a first male longitudinal end part intended to be inserted in a female housing of a stator casing equipped with an oil supply circuit of the tube, and a second male longitudinal end part around which is intended to be mounted a hydrodynamic bearing to guide the tube in the shaft, wherein the first end part includes a free annular end with a convex rounded cross-section intended to bear axially against an annular bottom of said housing, and in that said second end part comprises an outer axial annular bearing surface of an inner ring of the bearing, the annular bearing surface presenting in cross-section a convex curved shape.

A propeller control unit (PCU) has: a pitch angle actuator; a valve operable to selectively fluidly connect the pitch angle actuator with a source of oil for controlling pitch angles of blades of a propeller and with a drain line for draining oil out of the pitch angle actuator for feathering the blades; and a bypass line having an inlet hydraulically between the valve and an inlet of the drain line, the bypass line having an outlet hydraulically between the inlet of the drain line and an outlet of the drain line.

A braking system including a brake actuator, a control valve, a control assembly, and at least one pressure sensor. The control valve is disposed to direct hydraulic fluid to the brake actuator at a rate corresponding to a magnitude of a control signal. The control assembly includes a mixed-mode control system. The at least one pressure sensor is configured to measure a pressure of the hydraulic fluid to the brake actuator. The control assembly is configured to determine a position of the brake actuator. The mixed-mode control system is configured to determine a position command and a pressure command. The mixed-mode control system is configured to adjust the magnitude of the control signal based on at least one of the position command and the pressure command so as to reposition the brake actuator from a first position to a second position.

A Simulink modeling method for a mechanical hydraulic device of an aeroengine fuel regulator is proposed. The Simulink modeling method can implement high precision simulation of a mechanical hydraulic device of an engine fuel conditioning system, and greatly increase the simulation speed as compared with the existing modeling simulation in AMESim; solve the problem of a double-layered nested algebraic loop occurring when the mechanical hydraulic device is modeled in Simulink, and improve the simulation precision of the system. In addition, because of having certain universality, the resolving method for a double-layered nested algebraic loop can be generalized to resolve other types of algebraic loops. Meanwhile, the parameters of the simulation model provided by the present invention can be conveniently modified, and can provide a reference for modeling simulation of mechanical and hydraulic devices of engine fuel conditioning systems of other types.

A thrust reverser actuation system for a jet propulsion engine for a vehicle, the thrust reverser actuation system comprising: a plurality of hydraulically-driven thrust reverser actuators for actuating one or more thrust reverser components of the jet propulsion engine, each actuator comprising: a hydraulic circuit; and a bi-directional electrically-driven pump configured to pump hydraulic fluid through the hydraulic circuit, wherein the hydraulic circuit and the pump are configured such that the direction of the pump dictates the direction of the actuation of the actuator.

Disclosed is a high-speed section disconnect for a driven turbocharger with a traction drive. The turbo shaft is attached to a turbine and compressor, and interfaces with a high-speed traction drive. A mechanical coupling connects the traction drive to a transmission, which is connected to the engine so that power can flow to or from the turbo shaft, but the mechanical coupling can be selectively disconnected so that the high-speed section of the driven turbocharger can also be decoupled from the engine during certain operating conditions to reduce mechanical losses in the system.

Provided is a turbine having a turbine regulating unit, a turbine protection unit, at least one safety block, quick-closing valves and regulating valves, wherein the quick-closing valves and the regulating valves can be actuated by associated switching and setting drives, wherein the at least one safety block is a pneumatic safety block, and in that at least one switching drive for direct or indirect actuation of a quick-closing valve is a pneumatic switching drive. The embodiment also relates to a method for retrofitting an existing turbine having a turbine protection unit, a turbine regulating unit, a hydraulic safety clock, quick-closing valves and regulating valves, wherein the quick-closing valves can be actuated directly or indirectly by associated hydraulic switching drives.

A fuel supply system for a turbomachine, comprising a fuel circuit comprising pressurizer at the output of the circuit, a pump arranged to send into the circuit a fuel flow rate which is an increasing function of the rotational speed of a shaft of the pump, and a control circuit arranged to control the device to comply with a flow rate setpoint at the output of the fuel circuit. The system further comprises a feedforward corrector circuit configured to calculate an increment of the flow rate setpoint as a function of the engine speed of the turbomachine and of a variation in the engine speed of the turbomachine, and to add this increment to the flow rate setpoint. A method of regulating the pump is also described.

A rotating turbomachine provided with a fluid sealing device, comprising an extensible/dilatable bellows piston to make a sealing surface abut against a rotor disc, or against the head of the shaft, therefore confining the working fluid in the turbomachine stopped during the respective maintenance operations, is described. A coolant is supplied inside the bellows piston during the normal operations of the machine.

A projecting portion is formed on a nozzle ring, projects to a radially outer side with respect to a cylindrical portion, extends in a circumferential direction, and is held in abutment against a housing from a side of a link plate. A plate is faced to the nozzle ring on a side of a nozzle vane, and is configured to form a flow passage in a clearance to the nozzle ring. A pin is inserted into a first insertion portion formed in the nozzle ring and a second insertion portion formed in the plate, and to which the nozzle ring and the plate are mounted while the clearance is maintained. A counter bore groove is formed in the first insertion portion of the nozzle ring on the side of the link plate, and cut out the projecting portion.