Abstract: The present invention relates to a process for lubricating an aircraft engine, and preferably a turboreactor engine, comprising at least one shaft (2), in which the pressurization of oil taken from a reservoir (3), the distribution of the oil via a downstream circuit (5) to elements (6) of said engine, and the return of the oil via an upstream circuit (7) to the reservoir (3) are ensured by means of a pump (1, 15, 17), the rotational speed of said pump (1, 15, 17) being variable and adjustable, characterized in that this rotational speed of said pump (1, 15, 17) is preferably regulated by a predetermined law in order to adapt to the actual lubrication needs of said engine.

Abstract: An electricity generating system having a body (159), an annular combustor (14), a turbine (16), a compressor chamber and a compressor (102) positioned within the compressor chamber. An inlet port is in fluid communication with the compressor chamber and an exit port is in fluid communication with the turbine. A plurality of magnets (MG) is secured to the rotor (18) and a stator (22) made of mangnetically attracted material, such as iron, and having a stator winding provided in the body (159). The stator winding is positioned in close proximity to the plurality of magnets mounted to the rotor whereby rotation of the rotor (18) induces a current in the winding.

Abstract: The invention is embodied in a closed-cycle lubrication oil system used during turbine start-up to provide both lift oil and hydraulic oil from one system using a single variable volume pump that supplies fluid at a high pressure for lift oil requirements. The pump discharge pressure is reduced, through a pressure regulating/reducing valve, down to hydraulic system demands. During steady-state gas turbine operation, the system provides only a flow of hydraulic oil to position the inlet guide vanes and gas valves as required by the gas turbine controls logic. During gas turbine shut-down, the system again meets both lift oil and hydraulic oil requirements. A second pump is advantageously incorporated in the preferred embodiments of the system to provide 100% redundancy in providing either lift or hydraulic oil.

Abstract: A system for cooling the lubricant of the speed reducer of an aircraft turboshaft-engine during high-speed flight and during low-speed taxying. The cooling system includes a radiator through which the lubricant flows. An air supply duct delivers cooling air over the radiator. An air discharge duct discharges the air into the exhaust nozzle of the engine. The air supply duct is fed by an arcuate air take-off slot disposed in the air intake of the engine. The air discharge duct is provided with a flap for slowing air flow through the cooling system, and with an ejector-mixer, which is fed by compressed air, taken from the engine compressor, for creating a Venturi effect to increase air flow through the cooling system when required.

Abstract: The invention relates to an oil pump driven by a hydraulic motor, that is itself driven by fuel pumped by a remote fuel pump through the engine fuel line. The hydraulic fuel driven oil pump is particularly advantageous for use in a gas turbine engine, to reduce dependence on or completely eliminate the auxiliary gear box (AGB) conventionally used to mechanically connect various engine systems with an engine shaft. Separating the oil pump and other fuel/oil system components from the AGB enables the rationalization of these systems and allows designers to reconfigure systems into a compact unit including the oil pump, separator, oil tank, heat exchanger and filters for fuel and oil. Using pressurized fuel to hydraulically drive the oil pump frees the oil system from location restraints and operating limitations, and permits recovery of otherwise wasted energy from the fuel bypass circuit during idling and takeoff.