Abstract: A distributor valve comprising a second element configured to be displaced relative to a first element, so as to form an overall passage opening of variable fuel passage section corresponding to the intersection of a first passage opening and a second passage opening. The head portion of the second passage opening comprises a first inclination having a first average slope, the intermediate portion of the second passage opening comprises a second inclination having a second average slope strictly greater than said first average slope, and the foot portion of the second passage opening comprises a third inclination having a third average slope, strictly less than said second average slope.

Abstract: A fluid supply system (1) for turbine engine, includes a high pressure volumetric pump (4), a fluid metering device (6) and a control valve (8) configured to vary the flow rate of fluid in a bypass circuit (14) so as to regulate the pressure difference between an input and an output of the metering device (6). The control valve (8) includes an obturator, the variable position of which is measured by a sensor (20). An electronic regulation system (3) compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (14). The flow rate of the high pressure pump (4) is commanded so that the measured position of the obturator adapts to the position set-point.

Abstract: A distributor valve comprising a second element configured to be displaced relative to a first element, so as to form an overall passage opening of variable fuel passage section corresponding to the intersection of a first passage opening and a second passage opening. The head portion of the second passage opening comprises a first inclination having a first average slope, the intermediate portion of the second passage opening comprises a second inclination having a second average slope strictly greater than said first average slope, and the foot portion of the second passage opening comprises a third inclination having a third average slope, strictly less than said second average slope.

Abstract: The invention relates to a butterfly valve (24) for bleeding a compressor for an aircraft turbine engine, the valve including a valve body (32), a butterfly (36), and a device (42) for controlling the angular position of the butterfly, the device (42) including a mobile actuation member (64) connected to the butterfly by a link (70), the member (64) being subjected: to a first adjustable pressure force (F1) applied by air from the compressor, the first force (F1) returning the butterfly (36) to a closed position; and to a second mechanical force (F2) returning the butterfly (36) to an open position, and coming from an aerodynamic torque (C) applied by the air to the butterfly (36), of which the axis of rotation (38) is off-centre relative to the butterfly.

Abstract: A fuel metering unit comprising a movable element including at least one fuel flow section opening upstream towards a fuel supply duct and opening downstream towards a utilization duct through a metering slot with a flared profile having a narrow flow section and a wide flow section, the movable element able to be moved with respect to a stationary element between a low flow rate position and a high flow rate position, the metering slot made in the stationary element or in the movable element and its obstruction obtained by covering the slot with a wall of the movable element or of the stationary element.

Abstract: The invention relates to a device (11) for cooling oil for a turbine engine, such as an aircraft turbojet or turboprop engine, characterized in that it comprises a duct (12) for circulating a flow of cold air (F1), means (16) for injecting oil into the duct, and means (19) for extracting the oil mixed with the flow of cold air (F1), located in the duct (12), downstream from the injection means (16).

Abstract: A fluid supply system (1) for turbine engine, includes a high pressure volumetric pump (4), a fluid metering device (6) and a control valve (8) configured to vary the flow rate of fluid in a bypass circuit (14) so as to regulate the pressure difference between an input and an output of the metering device (6). The control valve (8) includes an obturator, the variable position of which is measured by a sensor (20). An electronic regulation system (3) compares the measured position of the obturator with a position set-point of the obturator determined as a function of a flight condition of the aircraft and/or a measured fluid temperature and corresponding to a fluid flow rate set-point in the bypass circuit (14). The flow rate of the high pressure pump (4) is commanded so that the measured position of the obturator adapts to the position set-point.

Abstract: A fuel metering unit comprising a movable element including at least one fuel flow section opening upstream towards a fuel supply duct and opening downstream towards a utilization duct through a metering slot with a flared profile having a narrow flow section and a wide flow section, the movable element able to be moved with respect to a stationary element between a low flow rate position and a high flow rate position, the metering slot made in the stationary element or in the movable element and its obstruction obtained by covering the slot with a wall of the movable element or of the stationary element.

Abstract: A turbomachine air starter, including a first compartment wherein non-overrunning elements of the air starter are situated, corresponding to elements which are only run in the turbomachine starting phase, and a second compartment wherein overrunning elements of the air starter are situated, corresponding to the elements which are run throughout an operating time of the turbomachine, including the starting phase. The first compartment includes an oil receptacle for oil splash lubrication of the non-overrunning elements, and the second compartment includes an AWC type oil cavity for lubrication of the overrunning elements supplied by the lubrication oil return of the overrunning elements, in turn supplied with pressurized lubrication oil supplied by the turbomachine, the receptacle and the cavity being internal to the air starter.

Abstract: The invention relates to a butterfly valve (24) for bleeding a compressor for an aircraft turbine engine, the valve including a valve body (32), a butterfly (36), and a device (42) for controlling the angular position of the butterfly, the device (42) including a mobile actuation member (64) connected to the butterfly by a link (70), the member (64) being subjected: to a first adjustable pressure force (F1) applied by air from the compressor, the first force (F1) returning the butterfly (36) to a closed position; and to a second mechanical force (F2) returning the butterfly (36) to an open position, and coming from an aerodynamic torque (C) applied by the air to the butterfly (36), of which the axis of rotation (38) is off-centre relative to the butterfly.

Abstract: A fuel metering unit including a movable element including at least one fuel passage section opening upstream towards a fuel supply conduit and opening downstream towards a conduit of use through a metering slot with a flared profile having a narrow passage section flaring as far as a wide passage section, the movable element being able to be moved with respect to a fixed element between a low flow rate position in which the metering slot is for a large part obstructed and a high flow rate position in which the metering slot is for a large part exposed, the metering slot being made in the fixed element or in the movable element and its obstruction being obtained by covering the slot with a wall of the movable element or of the fixed element.

Abstract: A fuel metering unit including a movable element including at least one fuel passage section opening upstream towards a fuel supply conduit and opening downstream towards a conduit of use through a metering slot with a flared profile having a narrow passage section flaring as far as a wide passage section, the movable element being able to be moved with respect to a fixed element between a low flow rate position in which the metering slot is for a large part obstructed and a high flow rate position in which the metering slot is for a large part exposed, the metering slot being made in the fixed element or in the movable element and its obstruction being obtained by covering the slot with a wall of the movable element or of the fixed element.

Abstract: The invention relates to a device (11) for cooling oil for a turbine engine, such as an aircraft turbojet or turboprop engine, characterised in that it comprises a duct (12) for circulating a flow of cold air (F1), means (16) for injecting oil into the duct, and means (19) for extracting the oil mixed with the flow of cold air (F1), located in the duct (12), downstream from the injection means (16).

Abstract: A gas turbine engine incorporating a starter mounted on the gear box is disclosed. The gas turbine engine includes an AGB gear housing mechanically connected with an engine shaft for driving auxiliary machines and an air starter mounted on the housing, the starter and housing enclosures being in communication such that the lubricating oil of the starter should be distributed from the AGB housing. The oil enclosure of the starter is pressurized by a source of air, being independent from the AGB housing. Advantageously, the pressurization air is taken from a pressurization enclosure of an engine bearing.

Abstract: A gas turbine engine incorporating a starter mounted on the gear box The present invention refers to a gas turbine engine, comprising an AGB gear housing (12) mechanically connected with an engine shaft for driving auxiliary machines and an air starter (10, 10?) mounted on the housing, the starter and housing enclosures being in communication such that the lubricating oil of the starter should be distributed from the AGB housing. The engine is characterized in that the oil enclosure of the starter (10, 10?) is pressurized by a source of air, being independent from the AGB housing. Advantageously, the pressurization air is taken from a pressurization enclosure of an engine bearing.

Abstract: A device for separating and filtering particles in a flow of contaminated fluid, the device including a casing having an inlet duct fitted with a cyclone separator designed to concentrate centrifugally particles in the inlet flow towards the periphery of the flow, a tubular element mounted in the casing with the upstream end of the element adjacent the inlet duct and having a diameter smaller than the inlet duct so that the substantially clean fluid from the cyclone separator flows into a central flow path within the tubular element and the contaminated fluid from the separator flows into a peripheral flow path between the tubular element and the casing, and a filter mounted in the casing adjacent an outlet duct so that the clean fluid in the central flow path passes through a central passage of the filter to the outlet duct and the contaminated fluid in the peripheral flow path is filtered by the filter to form a filtered flow which mixes with the clean fluid in the central passage whereby the fluid flow rat