Snecma

Snecma Moteurs

Alain Varizat

Jean-Marie Brocard

Philippe Galozio

Michel Martini

Alain Pierre Garassino

Regis Michel Paul Deldalle

Regis Deldalle

Christian Denis Le Boeuf

Alain Patrick Paya

Régis Deldalle

Jean-Marie Brocart

A fuel supply device includes a fuel supply pipe receiving fuel at a non-regulated pressure delivered by a pump, a device for measuring the flow rate of fuel in the pipe, a first controlled variable-restriction valve mounted in the supply pipe, a control system connected to the flow rate measurement device and to the first valve to control the valve to deliver fuel to the engine at a desired flow rate under normal operating conditions of the engine, a second controlled variable-restriction valve mounted in the supply pipe in series with the first valve, and a control for controlling the second valve to enable the engine to be supplied with fuel at an adjustable, reduced flow rate in response to detecting over-speed or over-thrust of the engine.

Device for supplying fuel to a gas turbine engine with regulated fuel flow rate

A centrifugal pump driven by mechanical coupling with an engine has a low pressure inlet receiving fuel from a fuel circuit of an aircraft, a high pressure outlet connected to a regulator circuit for regulating the flow rate of fuel supplied to the engine, and an assistance pump unit that is electrically controlled, having an inlet connected to the aircraft fuel circuit and an outlet connected to the flow rate regulator circuit so as to deliver, via its outlet, fuel that is at a predetermined minimum pressure, the pressure of the fuel supplied to the regulator circuit being the higher of the pressures delivered by the centrifugal pump and the assistance pump unit.

Aircraft engine fuel supply

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

Bois-le-Roi, France

Alain Varizat