Abstract: A cover for a rotating electric machine includes an axis of rotation (X), the cover being designed to be arranged on an inverter of the machine. The cover includes a skirt extending in a radial direction and forming a perimeter of the cover, the perimeter defining an inner portion of the cover and an open area arranged in the inner portion and comprising at least one axial opening. The open area extends over at least 50% of the inner portion of the cover.

Abstract: A winding for an active portion of a rotary electric machine has at least one phase system including a plurality of phases each including a first energizing pin and a second energizing pin each forming a phase input or output. Each energizing pin includes an energizing end that extends out of the slot and each energizing end that forms a phase output being electrically connected to an energizing end that forms a phase input of a different phase, in order to achieve a delta configuration. The winding includes a first set including at least one energizing end forming a phase input and at least one other energizing end forming a phase output, and a second set including at least one energizing end forming a phase input and at least one other energizing end forming a phase output.

Abstract: A winding for an active part of a rotary electric machine having at least one phase system. The winding includes a plurality of phases each including a first power supply pin and a second power supply pin each forming a phase input or output, each power supply pin including a power supply end that extends outside the slot and extends a conductive segment that extends inside the slot. At least one portion of a first power supply end is arranged on an inner periphery of the winding, the first end extending a conductive segment arranged in an external layer and at least one portion of a second power supply end is arranged on an outer periphery of the winding, said second end extending a conductive segment arranged in an internal layer, the inner periphery being closer to the axis than the outer periphery and the internal and external layers forming edge layers.

Abstract: A slide for a fuel circuit valve of an aircraft engine extending along a longitudinal axis, and comprising a narrowed intermediate portion extending between two cylindrical end portions, a first end portion being separated from the narrowed intermediate portion by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate portion including in turn, as an extension of the shoulder, at least one cylindrical portion, the shoulder comprising at least one groove which extends radially from the cylindrical surface of the first end portion, towards the longitudinal axis, and which forms a fuel recirculation area which provides the generation of a jet of fuel on the cylindrical portion of the narrowed intermediate portion, when fuel flows along the first end portion towards the narrowed intermediate portion and the second end portion.

Abstract: A spool for a fuel circuit valve of an aircraft engine, extending along a longitudinal axis and including a narrowed intermediate section extending between two end cylindrical sections, a first end section being separated from the narrowed intermediate section by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate section also including, extending away from the shoulder, at least one cylindrical portion, and the shoulder is provided with a step extending away from the cylindrical surface of the first end section which, when the fuel flows along the first end section towards the narrowed intermediate section and the second end portion, generates a jet of fuel on the cylindrical portion of the narrowed intermediate section, a recirculation of fuel forming in an area in front of the shoulder.

Abstract: The invention concerns a fuel system (1) for a turbomachine comprising: —a control circuit (9a), —a main circuit (9b), —a flow rate regulator (2), suitable for regulating the flow of fuel in the control circuit (9a) and in the main circuit (9b) depending on the speed of the turbomachine, and —a drain tank (4) being designed to draw fuel from, store fuel in and drain fuel into the main circuit (9b) on the basis of the pressure difference between the main circuit (9b) and the tank (5) or the high-pressure pump (6) to which it is connected.

Abstract: A combustion chamber for a turbomachine that includes a chamber end wall and a plurality of air and fuel injection systems distributed circumferentially about an axis of the combustion chamber. The combustion chamber includes, associated with each injection system, a guide device for guiding an airflow including at least one wall mounted on the injection system and projecting in the upstream direction, one wall acting as an obstacle to a circumferential flow of air around the axis. The one wall of the guide device for guiding the airflow has a shape substantially defining a quarter of a spheroid the interior volume of which forms a guide scoop for guiding the airflow feeding the combustion chamber.

Abstract: A spool for a fuel circuit valve of an aircraft engine, extending along a longitudinal axis and including a narrowed intermediate section extending between two end cylindrical sections, a first end section being separated from the narrowed intermediate section by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate section also including, extending away from the shoulder, at least one cylindrical portion, and the shoulder is provided with a step extending away from the cylindrical surface of the first end section which, when the fuel flows along the first end section towards the narrowed intermediate section and the second end portion, generates a jet of fuel on the cylindrical portion of the narrowed intermediate section, a recirculation of fuel forming in an area in front of the shoulder.

Abstract: A slide for a fuel circuit valve of an aircraft engine extending along a longitudinal axis, and comprising a narrowed intermediate portion extending between two cylindrical end portions, a first end portion being separated from the narrowed intermediate portion by a shoulder having a surface arranged overall perpendicular to the longitudinal axis, the narrowed intermediate portion including in turn, as an extension of the shoulder, at least one cylindrical portion, the shoulder comprising at least one groove which extends radially from the cylindrical surface of the first end portion, towards the longitudinal axis, and which forms a fuel recirculation area which provides the generation of a jet of fuel on the cylindrical portion of the narrowed intermediate portion, when fuel flows along the first end portion towards the narrowed intermediate portion and the second end portion.

Abstract: A combustion chamber for a turbomachine that includes a chamber end wall and a plurality of air and fuel injection systems distributed circumferentially about an axis of the combustion chamber. The combustion chamber includes, associated with each injection system, a guide device for guiding an airflow including at least one wall mounted on the injection system and projecting in the upstream direction, one wall acting as an obstacle to a circumferential flow of air around the axis. The one wall of the guide device for guiding the airflow has a shape substantially defining a quarter of a spheroid the interior volume of which forms a guide scoop for guiding the airflow feeding the combustion chamber.

Abstract: The invention concerns a fuel system (1) for a turbomachine comprising: —a control circuit (9a), —a main circuit (9b), —a flow rate regulator (2), suitable for regulating the flow of fuel in the control circuit (9a) and in the main circuit (9b) depending on the speed of the turbomachine, and —a drain tank (4) being designed to draw fuel from, store fuel in and drain fuel into the main circuit (9b) on the basis of the pressure difference between the main circuit (9b) and the tank (5) or the high-pressure pump (6) to which it is connected.