Abstract: The invention relates to a process for treating a metal alloy part, characterized in that it comprises the following steps: —producing a stock formulation by mixing, in equal molar parts of silicon, an alcoholic solution of hydrolysed epoxysilane and an alcoholic solution of hydrolysed aminosilane, —mixing the stock formulation with a suspension comprising conductive nanowires in an amount by weight of between 0.1% and 10% relative to the total weight of the stock formulation in order to obtain a dilute formulation, and —depositing the dilute formulation on the part in order to obtain the coating.

Abstract: The invention relates to a fuel injector for a turbine engine, comprising a body having a fuel inlet opening into an upstream chamber and a fuel outlet connected to a downstream chamber, a metering valve being mounted between the upstream chamber and the downstream chamber, said valve being subjected to the action of an elastic return spring tending to return the valve to a closed position, the spring (11) and the valve being designed to allow the opening of the valve and to allow the passage of fuel from the upstream chamber to the downstream chamber, above a given fuel pressure in the upstream chamber, the return spring (11) extending along the axis (X) of movement of the valve, characterized in that the spring (11) has a first axial end and a second axial end, both annular, connected to one another by at least two helical parts (11c, 11d) elastically deformable in the axial direction (X).

Abstract: An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.

Abstract: The invention relates to a process for treating a metal alloy part, characterized in that it comprises the following steps: —producing a stock formulation by mixing, in equal molar parts of silicon, an alcoholic solution of hydrolysed epoxysilane and an alcoholic solution of hydrolysed aminosilane, —mixing the stock formulation with a suspension comprising conductive nanowires in an amount by weight of between 0.1% and 10% relative to the total weight of the stock formulation in order to obtain a dilute formulation, and —depositing the dilute formulation on the part in order to obtain the coating.

Abstract: The present invention relates to a method for differentiating control failures in a system for controlling an actuator (14) determining the position of a member for modifying the state of a gas-turbine engine, the system including a single- or dual-channel electric control and a mechanical control, the electric control including one computer (10, 10?) per channel, only one of which is active at any given time in order to calculate the set position of the movable member of the actuator (14) and to transmit a set signal to the single-channel mechanical control of the actuator, a failure being diagnosed when a deviation is detected between the set position of the movable member of the actuator and the position thereof measured during a predetermined deviation confirmation time.

Abstract: An arrangement for an aircraft turbine engine combustion chamber including an injection system and a fuel injector is provided. The injection system includes an injector nozzle guide, the inner surface of which delimits an opening for centering the nozzle, which includes an outer casing. The arrangement further includes a sealing device between the inner surface of the guide and the outer casing. The sealing device includes a first part accommodated in a groove of the outer casing, the groove being delimited, in part, by a downstream delimiting surface, the first part having a first sealing surface and bearing axially against the downstream delimiting surface; and a second part having a second sealing surface bearing radially against the inner surface of the guide.

Abstract: A fuel injector for a turbine engine, the injector including a body including a mechanism for admitting fuel under pressure, a stop valve for feeding a primary fuel circuit, and a metering valve mounted downstream from the stop valve for feeding a secondary fuel circuit. The injector further includes at least one leakage channel, that can be formed by a thread, that extends from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary circuit.

Abstract: A fuel injector for a turbine engine, the injector including a body including a primary fuel circuit and a secondary fuel circuit fed by a metering valve. A leakage channel extends from a zone in fluid flow connection with the primary circuit to a zone in fluid flow connection with the secondary circuit. The leakage channel is configured to be open in a closed position of the metering valve and to be closed by the metering valve moving.

Abstract: A fuel injector for a turbine engine, the injector including a body including a primary fuel circuit and a secondary fuel circuit fed by a metering valve. A leakage channel extends from a zone in fluid flow connection with the primary circuit to a zone in fluid flow connection with the secondary circuit. The leakage channel is configured to be open in a closed position of the metering valve and to be closed by the metering valve moving.

Abstract: The present invention relates to a method for differentiating control failures in a system for controlling an actuator (14) determining the position of a member for modifying the state of a gas-turbine engine, the system including a single- or dual-channel electric control and a mechanical control, the electric control including one computer (10, 10?) per channel, only one of which is active at any given time in order to calculate the set position of the movable member of the actuator (14) and to transmit a set signal to the single-channel mechanical control of the actuator, a failure being diagnosed when a deviation is detected between the set position of the movable member of the actuator and the position thereof measured during a predetermined deviation confirmation time.

Abstract: A fuel injector for a turbine engine, the injector including a body including a mechanism for admitting fuel under pressure, a stop valve for feeding a primary fuel circuit, and a metering valve mounted downstream from the stop valve for feeding a secondary fuel circuit. The injector further includes at least one leakage channel, that can be formed by a thread, that extends from a zone situated downstream from the stop valve and upstream from the metering valve to a zone situated downstream from the metering valve to generate a permanent leakage flow in the secondary circuit.

Abstract: A fuel supply installation for a turbojet including two volumetric pumps for combining their flow rates is disclosed. The pumps include a main pump dimensioned for the full gas rate and an auxiliary pump controlled and dimensioned to provide the supplementary flow rate necessary on ignition.

Abstract: Optimisation of components of a fuel supply installation for a turbojet. The installation comprises two volumetric pumps for combining their flow rates, a main pump (14) dimensioned for the full gas rate and an auxiliary pump (16) controlled and dimensioned to provide the supplementary flow rate necessary on ignition.

Abstract: This injector with two valves (7, 10) which open at different fuel pressures so as to establish a primary flow regime and then a secondary flow regime is characterized in that the primary regime is enriched with fuel via an orifice (21) which adds a branch to the primary flow path of the fuel, but which is closed when the secondary valve is displaced so as to prevent enrichment of the fuel in the secondary regime. This invention applies in particular to certain aircraft engines.

Abstract: This injector with two valves (7, 10) which open at different fuel pressures so as to establish a primary flow regime and then a secondary flow regime is characterized in that the primary regime is enriched with fuel via an orifice (21) which adds a branch to the primary flow path of the fuel, but which is closed when the secondary valve is displaced so as to prevent enrichment of the fuel in the secondary regime. This invention applies in particular to certain aircraft engines.

Abstract: A boat and propulsion system especially useful for shallow water operation. A boat, such as a flat bottom fishing boat, is provided with a lowered transom and a platform attached to the transom which extends upwardly at an angle along the sides of the boat to define a well area which receives and drains any backwash. An air cooled internal combustion engine is provided with a straight propeller shaft and propeller attached thereto. A motor plate rigidly attached to the engine may be removably mounted on a swivel-hinge assembly mounted on the platform to allow double axis movement of the engine and propeller in relation to the platform. This provides for a thrusting position with the propeller in the water and a neutral position with the propeller held above the water. A control handle may be removably connected to the motor plate to provide one handed steering and throttle control by the operator.

Abstract: A boat and propulsion system especially useful for shallow water operation. A boat, such as a flat bottom fishing boat, is provided with a lowered transom and a platform attached to the transom which extends upwardly at an angle along the sides of the boat to define a well area which receives and drains any backwash. An air cooled internal combustion engine is provided with a straight propeller shaft and propeller attached thereto. A motor plate rigidly attached to the engine may be removably mounted on a swivel-hinge assembly mounted on the platform to allow double axis movement of the engine and propeller in relation to the platform. This provides for a thrusting position with the propeller in the water and a neutral position with the propeller held above the water. A control handle may be removably connected to the motor plate to provide one handed steering and throttle control by the operator.