Safran Aircraft Engines

Snecma Moteurs

Snecma

Hispano Suiza

Safran Transmission Systems

Alain Pierre Garassino

Bellal Waissi

Claude M Maillard

David Maillard

Jean-Marie Brocard

Stéphane Prunera-Usach

Jordane Peltier

Sébastien Christophe Chalaud

Mathieu Jean Pierre Trohel

Marc Missout

Nuria Llamas Castro

Lambert Olivier Marie Demoulin

Alain Varizat

Olivier Robert Michel Delepierre-Massue

Isabelle Vegiotti

Christian Denis Le Boeuf

Frantz Armange

Alain Patrick Paya

Caroline Dessenne

Claude Marcel Maillard

Claude Maillard

Isabelle Vergiotti

Stephane Prunera-Usach

Jordanne Peltier

A control system for controlling the pitch of a propeller, the system including a propeller shaft, a blade swivel device having a rotary control element suitable for placing the blades in an angular position corresponding to a desired propeller pitch, and a transmission presenting an outlet member coupled in rotation with the rotary control element of the blade swivel device. The transmission includes a variable speed drive having drive, control, and outlet rotors that are coupled in rotation respectively with the propeller shaft, with a control member, and with the outlet member of the transmission. With the variable speed drive, the speed of rotation of the outlet member of the transmission is a predetermined function of the speeds of rotation not only of the propeller shaft, but also of the control member.

Propeller pitch control system

A turbomachine or a turbojet engine or a turboprop engine of an aircraft, including at least one oil circuit and a cooling mechanism including a refrigerant circuit including a first heat exchanger configured to exchange heat between the refrigerant and air and forming a condenser, a second heat exchanger configured to exchange heat between the refrigerant and the oil of the oil circuit and forming an evaporator, an expander mounted downstream from the first exchanger and upstream from the second exchanger, in a direction in which the refrigerant circulates, and a compressor mounted downstream from the second exchanger and upstream from the first exchanger.

Cooling of an oil circuit of a turbomachine

A multi-body gas turbine engine, especially an aircraft engine, comprising at least one low-pressure rotating body, a high-pressure rotating body, and a starter designed to rotate the high-pressure body in order to start the engine, wherein the starter is coupled to the low-pressure body and the engine comprises a first disengageable coupling device disposed between the low-pressure body and the high-pressure body, for rotatably connecting the high-pressure body to the low-pressure body so as to allow the starting of the engine by means of the starter.

Gas turbine engine comprising a starter engaged with a low-pressure body

A gearbox to be mounted on a turbomachine and driven by a radial drive shaft of the latter. The gearbox has a three-dimensional or sinuous shape, which can house a large quantity of equipment to be driven, without occupying a large amount of space in any dimension, since the gearbox remains close to the turbomachine and the equipment can be distributed over a large surface. The drive train of gears successively extends into several non-parallel planes and comprises an axial branch on the turbomachine and a branch forming an arc of circle around the turbomachine.

Drive gearbox on a turbomachine, consisting of a drive train with gear lines extending into non-parallel planes

A fuel injection system in a turbomachine, the system comprising a high pressure pump for pressurizing the fuel coming from a fuel tank to a high pressure P , a plurality of fuel injectors disposed in a combustion chamber of the turbomachine, and a metering unit interposed between said high pressure pump and said plurality of injectors to control the rate at which fuel flows into the injectors from the high pressure pump, wherein said metering unit comprises a pressurization valve piloted to occupy two pressure levels by means of a metering valve fed with fuel from said high pressure pump. A solenoid stop valve for acting on the pressurization valve is also provided to interrupt the feed of fuel to the injectors.

Two-level pressurization valve controlled by a fuel metering unit

In a turbomachine whose speed of rotation is controlled by means of a throttle control lever acting via an electronic control circuit, a system is provided to provide protection against excess speed, the system comprising means for limiting the fuel feed of the turbomachine to a predetermined fixed flow rate Wps when the speed of rotation exceeds an authorized maximum speed, means for maintaining said fuel feed at said predetermined fixed flow rate while the speed of rotation drops below the authorized maximum speed, and means for reducing said fuel speed to a flow rate Wr corresponding to an idling speed when the throttle control lever issues an idling control to the turbomachine via the electronic control circuit.

Hydromechanical system for limiting excess engine speed

A hydraulic fuel control unit ( ) for an aircraft engine comprises means ( ) for controlling cutoff on stop and cutoff on overspeed of a fuel flow transferred by an output ( ) to the engine injectors. A logic module ( ) controls the position of a state switch ( ) into a test position or a normal position. The state module is managed such that the operation of the overspeed module can be tested each time the system is started on the ground. The architecture of the hydraulic unit ( ) is such that operation of the cutoff on stop can be tested during each landing. Correct operation in the overspeed test and in the cutoff on stop test is observed by detecting a difference between a control value ( ) of an allowable fuel flow that depends mainly on the engine speed, and a real flow value detected by sensors ( ).

Self-testable architecture for overspeed limitation and cutoff systems when the turbojet stops

Growing community of inventors

Crisenoy, France

Alain Pierre Garassino