Safran Power Units

Microturbo Sa

Safran Aircraft Engines

Safran

Safran Helicopter Engines

Mbda France

Roxel France

Jean-Francois Rideau

Fabien Silet

Olivier Bedrine

Patrick Marconi

Nicolas Claude Parmentier

Bruno Thoraval

Pierre Froment

Pascal Dauriac

Andre Pfiffer

Florent Dalmas

Gilles Aime Yann Guyader

Jean-Francois Doualle

The invention concerns a structure () for feeding air to an auxiliary power unit () of an aircraft () comprising a pressurized cabin () and an auxiliary power unit (), the structure comprising: a pipe () for feeding air to the auxiliary power unit; a unit () for controlling the airflow fed to the auxiliary power unit; and a valve () for the intake of air outside the aircraft, disposed at the inlet of the feed pipe (), the opening of the valve being driven by the control unit (). The structure is characterized in that it further comprises a circuit () for injecting air from the pressurized cabin into the auxiliary power unit feed pipe. The invention also concerns a method for feeding air to an auxiliary power unit.

Structure for feeding air to an auxiliary power unit in an aircraft

The invention concerns a method for generating auxiliary power in an aircraft, comprising the step consisting of: starting up an auxiliary power unit () of the aircraft by supplying compressed air to the auxiliary power unit () from a supercharger (), and transferring non-propulsive energy from the auxiliary power unit () to the aircraft. The invention also concerns a system () for generating auxiliary power in an aircraft and an aircraft implementing such a method.

Method and system for generating auxiliary power in an aircraft

An aircraft turboprop engine () including at least a low-pressure body () and a high-pressure body (), possibly also an intermediate-pressure body. At least one of the bodies includes a compressor. The low-pressure body drives a first gearbox () The turboprop engine also includes at least one load compressor () for supplying air to an air-conditioning circuit of an aircraft cabin. A rotor () of the load compressor is coupled to the low-pressure body. The load compressor () includes an air inlet () connected to a conduit () to bleed air from the compressor of the turboprop engine when all of the aforementioned bodies include only a single compressor, or from the compressor of the low-pressure body or the compressor of the intermediate-pressure body of the turboprop engine when all of the bodies include at least two compressors.

Supply of air to an air-conditioning circuit of an aircraft cabin from its turboprop engine

A method and architecture to optimize an entire traction system available on a helicopter by using an auxiliary engine to provide energy to equipment and accessories of the helicopter connected to the engines. Main engines and an APU unit, as an auxiliary engine, include a gas generator connected to, for the main engines, a reduction gearbox and an accessory gearbox for mechanical, electrical, and/or hydraulic power take-off and connected to, for the APU unit, at least one power conversion member. The power conversion member of the APU unit is connected to the equipment and accessories by the reduction gearbox and/or the accessory gearbox of the main engines.

Method and architecture for the optimized transfer of power between an auxiliary power motor and the main engines of a helicopter

A method for managing an electrical power supply system () of an aircraft, the power supply system () comprising at least one distribution bus arranged so as to power the electrical loads, at least one generator (G, G) of a propulsion engine of the aircraft, at least one engine-class main power unit (MPS, MPS), a plurality of contactors (C-C) which are capable of electrically connecting the distribution buses to the propulsion engine generator (G, G) and/or the main power unit (MPS, MPS); and a management module which is capable of controlling the contactors (C-C), a method wherein, during normal operating conditions of the aircraft, the distribution bus is powered by the engine-class main power unit (MPS, MPS) and, during the back-up operating mode of the aircraft, the distribution bus is powered by the propulsion engine generator (G, G).

Method for managing the electric power network of an aircraft

A system for supplying compressed air to a pneumatic network includes a load compressor, an air supply and a power shaft driving the load compressor. The system also includes in an air outlet of such load compressor, a connecting channel connected, on the one side, with a channel connected with the pneumatic network and, on the other side, with an air discharge conduct towards an exhaust nozzle. Air flow rate bleed valves are controlled by a processing unit via servo-loops as a function of the pressure sensors and the speed sensor.

Controlling method and system for compressed air supply to a pneumatic network, in particular in an aircraft

A propulsion system including: a booster; a turbojet engine; the booster including a chamber which is fixed to a rear casing of the turbojet engine by being arranged along the longitudinal axis thereof, which chamber includes at a rear a jet pipe and includes at least one charge and a mechanism initiating the charge; and gas bleed tubes connected to the booster and which are configured either for igniting the combustion chamber of the turbojet engine on for starting the turbine of the turbojet.

Growing community of inventors

Tournefeuille, France

Jean-Francois Rideau