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

Yves R Halin

Rene M Hersen

Eric C Pean

Jacques R LeLandais

A fuel injection supply circuit including a main filter situated between a low pressure pump and a high pressure pump, and a fuel metering device for supplying a metered flow of fuel to the fuel injectors, is provided with a self-cleaning filter downstream of the high pressure pump such that a first portion of the fuel flow received by the self-cleaning filter is filtered to provide a clean flow of fuel to the fuel metering device and the excess portion of the received fuel flow passes through the center of the self-cleaning filter and is returned, via a control valve, to the circuit upstream of the main filter.

Fuel injection supply circuit for providing a metered decontaminated

A fuel supply system for a gas turbine engine is disclosed which incorporates a discharge conduit into the fuel supply system such that an increase in the temperature of the fuel in the fuel injector conduits after engine shut-down will cause a valve in the discharge line to open before the opening of the valve in the fuel injector conduit, thereby directing excess fuel to a receiver or a tank, rather than into the hot combustion chamber. A fuel flow valve is connected to the fuel supply conduit, the discharge conduit, as well as the fuel injector conduits. Under normal operating conditions, a valve member within the fuel flow valve is positioned so as to enable communication between the fuel feed conduit and the fuel injector conduits so that fuel may be supplied to the fuel injectors. When the valve element is moved the a second position, after engine shut-down, it seals off the fuel feed conduit and enables communication between the fuel injector conduits and the discharge conduit. A valve in the discharge conduit is set so as to open at a slightly lower pressure than are the valves in the fuel injector conduits such that, if the fuel remaining in the fuel injector conduits is heated, its rise in pressure will cause the discharge valve to open before the opening of the fuel injector valve. Thus, a portion of the heated fuel may then be directed to a receiver or a tank.

Fuel supply system for a gas turbine engine

The circuit of the present invention is able to detect and identify the position of several contactors. Each contactor (1) is mounted in series with a resistor (2). The first contacts (A.sub.N) are interconnected. The same applies for the second contacts (B.sub.N) and the third points (C.sub.N) of the branches established. In addition, the third points (C.sub.N) are separated by a second resistor (6). The measuring of the voltage between the first and third points (A, C) makes it possible to detect and identify the open and closed contactors and in addition is able to detect a malfunction. Application for detecting the position of the doors of a thrust reverser of a turbojet engine.

Circuit for detecting the position of several bipolar contactors and

A thrust reverser safety system for a turbofan engine is disclosed which is integrated into the hydraulic control system of the thrust reverser door so as to prevent the hydraulic actuator from permitting the thrust reverser door to be forced into its deployed, thrust reversing position. The hydraulic actuator defines a closing chamber which, when acted upon by pressurized hydraulic fluid, urges the thrust reverser door to its closed, forward thrust position. The safety system according to this invention provides a valve associated with the hydraulic control circuit and the closing chamber which prevents the hydraulic fluid from being forced out of the closing chamber. This positively prevents the thrust reverser door from moving to its deployed, thrust reversing position. The valve allows pressurized fluid to pass into the closing chamber so that the thrust reverser door may be normally actuated when desired, but prevents the withdrawal of the pressurized fluid from this closing chamber when the thrust reverser door has been fully closed.

Thrust reverser safety system

Device for the detection of the position of the thrust reverser of a turbojet engine and its locking element, which includes an element integral with the moving part of the reverser, which cooperates with a mechanical locking device and a stationary electrical detection device for detecting the position of an element integral with the reverser and its locking device. The locking device, mounted pivotingly on a support element has on one side of a pivoting axle an arm which is connected with a control cylinder and on the other side a strap having an axle which may be engaged by a hook of the element integral with the moving part of the reverser, moving in a rectilinear motion of translation, the locking device carrying another axle parallel to its pivoting axle and upon which a lever is articulated.

Device for the detection of the position of the thrust reverser of a

Device for hydraulic control of thrust reversal units activated by jacks in jet engine. The jacks are connected to a rotary hydraulic engine fed by a hydraulic circuit which involves a mechanism for slowing down the speed of the reversal units when they approach the stop units. The hydraulic circuit allows for directly subjecting the engine's capacity to the opposing load on the engine. Application of this invention is possible to a dual flow turbojet in which the reversal units rotate in the cold flow.

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Saint Germain Les Corbeil, France

Yves R Halin