Safran Nacelles

A method for draping fibrous structures on a draping shape including at least one developable portion, the fibrous structures including fibers extending in a determined direction, wherein the fibrous structures are deposited on the draping shape so that the fibers of the fibrous structures overlap at straight lines of the developed surface of the developable portion of the draping shape.

An exhaust cone for an aircraft turbomachine, extending along a longitudinal axis and having a radially internal annular wall and a radially external skin delimiting a primary flow path for hot gases and surrounding the internal annular wall, and partitions mounted radially between the external skin and the internal annular wall and intersecting them in a manner that together with the skin and wall delimits acoustic chambers. The exhaust cone can further include at least one seal arranged between a radial end of one of the partitions and at least one among the internal annular wall and the external skin.

A gas turbine engine including a turbomachine. The turbomachine including a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine including an inlet duct defining an engine inlet, a fan duct defining a fan duct inlet, and a core duct defining a core duct inlet. The gas turbine engine including a fan cowl disposed circumferentially around the turbomachine and a heat exchanger defining a portion of the fan duct. At least a portion of the heat exchanger formed integrally with or coupled to the fan cowl.

A thrust reverser comprises: a stationary structure and a movable structure mounted opposite an opening; an actuator for selectively moving the movable structure between a direct jet position and a thrust reversal position; wherein the thrust reverser comprises a device for measuring a distance between a first measurement point and a second measurement point which is rigidly connected to the movable structure, and one of the measurement points comprises an emitter of a wave flow and the other one of the measurement points comprises a reflector element of at least a portion of the wave flow.

A method for controlling the application of a patch can include the following steps: positioning a patch on a surface to be covered by means of a gripper and with or without partial overlapping with adjacent patches; acquiring by means of an optical control means at least one image of the positioned patch; detecting defects in the positioning of the patch by identifying differences in the thickness of the patch on the surface to be covered based on the at least one image of the positioned patch; and mapping the defects in the positioning of the patch.

A lock system for a turbine engine nacelle, having: a support supporting a hook a three-point lock, a yoke and a three-point mechanism hingedly connected to a point of the support; and an actuating handle for actuating the mechanism between the locked and unlocked positions. Where the actuating handle can be connected to the three-point mechanism and a locking bush to pivot between a first end position when the three-point mechanism is locked and a second end position when the three-point mechanism is unlocked, and where the lock system includes a blocking tool to move the locking bush between a blocked position and an unblocked position when the bush is in the first end position, and to prevent the actuating handle from moving while the bush is in the blocked position.

A locking system for an aircraft nacelle is provided. The locking system includes a first portion configured to be mounted on a first part of an aircraft nacelle, and a second portion configured to be mounted on a second part of the aircraft nacelle. The locking system can be configured such that, when it is in the closed position, the first portion and the second portion are held together. The locking system further includes at least one buffer part and a load sensor joined together and configured to compress the load sensor between the buffer part and another part of the locking system when the locking system is in the closed position.

Said device ( 16 ) for controlling an electrical thrust reverser control system ( 1 ) for an aircraft comprises electrical supply means ( 9 ) and control means ( 19 ) which are configured to couple the electrical supply means ( 9 ) to the electrical control system ( 1 ) when the aircraft is on the ground and to uncouple the electrical supply means ( 9 ) from the electrical control system ( 1 ) when the aircraft is flying.

A seal configured to be interposed between a first and a second element of a propulsion assembly in an assembled configuration, the seal having a segment with an irregular reinforcement extending over at least a part of the length of the seal and which has a contour comprising a first contour part provided with a first reinforcement part, and a second contour part in which said first reinforcement part is absent, such that the second contour part has an increased susceptibility to buckling by comparison with the first contour part.

A sound attenuation panel for an aircraft turbomachine includes first and second skins and a core comprising. The core has at least one polygonal cell provided with an internal cavity in communication with at least one hole formed in the first wall. The cavity has a first height (H 1 ) between the first and second skins. Each cavity includes at least one internal partition that extends substantially from the first skin perpendicular to the first and second skins over a second height (H 2 ) that is less than the first height (H 1 ) and transversely between two side walls of the cell. The internal partition divides the cavity into at least two adjacent pockets in communication with one another and with the hole.