Societe Nationale D'etude Et De Construction De Moteurs D'aviation

Pierre G Hebert

Jean-Marie Brocard

Alain Tiepel

Claude M Maillard

Eric C Lorne

Franck Liotte

Guy D'Agostino

Eric C Pean

Guy R Hebraud

Michel P Dehu

Guv d'Agostino

Thierry N De Jongh

A rotary valve assembly is disclosed in which a rotary valve member is located within a casing having one or more fluid inlets and a plurality of fluid outlets. The rotary valve member has a fluid conduit which extends in a generally radial direction and which communicates with the fluid inlet. Fluid orifices communicate with the fluid conduit and exit through opposite sides of the rotary valve member to thereby minimize, or eliminate altogether, axial forces acting on the rotary valve member. Fluid outlet passages communicate with the two fluid orifices during at least pan of the rotation of the rotary valve member to direct the pressurized fluid to the valve outlets. The rotary valve may include a pair of rotary valve members drivingly connected to each other such that they rotate synchronously. The connection may include gear teeth formed on the adjacent peripheries of the rotary valve members such that rotation of one of the valve members causes rotation of the other. Each valve member may have a separate fluid inlet and separate fluid outlets.

Rotary valve assembly

A rotary valve assembly is disclosed in which a rotary valve member is located within a casing having one or more fluid inlets and a plurality of fluid outlets. The rotary valve member has a fluid conduit which extends in a generally radial direction and which communicates with the fluid inlet. Fluid orifices communicate with the fluid conduit and exit through opposite sides of the rotary valve member to thereby minimize, or eliminate altogether, axial forces acting on the rotary valve member. Fluid outlet passages communicate with the two fluid orifices during at least part of the rotation of the rotary valve member to direct the pressurized fluid to the valve outlets. The rotary valve may include a pair of rotary valve members drivingly connected to each other such that they rotate synchronously. The connection may include gear teeth formed on the adjacent peripheries of the rotary valve members such that rotation of one of the valve members causes rotation of the other. Each valve member may have a separate fluid inlet and separate fluid outlets.

A system for supplying fuel to a plurality of fuel injectors of a gas turbine engine is disclosed having first and second fuel distributors and a fuel transfer device which enables fuel to flow from the fuel source to the first and second fuel distributors as a function of the fuel flow rate. The fuel transfer device enables fuel to flow through the first fuel distributor under low fuel flow conditions. The first fuel distributor sequentially supplies fuel to each of a plurality of groups of fuel injectors when the fuel flow rate is below a predetermined threshold value. When the fuel flow exceeds a high threshold value, the fuel transfer device enables fuel to flow through the second fuel distributor which supplies fuel to all of the fuel injectors of the engine.

Fuel supply system for gas turbine engines

A control system for hydraulically controlling variable engine structures is disclosed in which the control system utilizes hydraulic fluid identical to that used by the aircraft hydraulic control circuit. A high pressure hydraulic pump, driven by the aircraft engine, may be interconnected with the aircraft hydraulic control circuit, or may be associated with a separate fluid reservoir, to supply pressurized hydraulic fluid to the actuators for controlling the variable engine structures. The engine control circuit also includes a hydraulic pressure modulator to modulate the pressure of the fluid supplied to the actuator and a selector connected between the high pressure pump and, the modulator and the aircraft control circuit to selectively supply the high pressure hydraulic fluid from the pump to either the engine control circuit, or to the aircraft control circuit. An electronic control system, which may comprise the aircraft computer, controls the operation of the selector as well as other parameters of the system.

Hydraulically actuated aircraft engine control system

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Libourne, France

Pierre G Hebert