Abstract: Turbojet engine nacelle (1) comprising an air intake structure (4) able to channel a flow of air towards a fan of the turbojet engine, and a central structure (5) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel (40) incorporating an air intake lip (4a) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (1), and a maintenance position in which the outer panel (40) is set away from the outer structure of the central section and the air intake lip (4a) is set away from the inn

Abstract: This maintenance trolley (17) for the air intake (9) of the nacelle of an aircraft turbojet engine is notable in that it comprises a base (19) and a platform (23) cantilever-mounted on this base (19) and designed to enter said air intake (9) without contact therewith.

Abstract: The invention relates to an air intake for an aircraft nacelle that includes a shroud that can be mounted on the fan casing of a turbojet engine. The shroud is sized so as to define a circumferential gap relative to the casing. Punctual linking means between the shroud and the casing are discretely distributed at the periphery of the shroud.

Abstract: A seal assembly for a turbojet nacelle includes a first end fastened to a first structure, and a second end contacting against a bearing zone of a second structure. The seal assembly further includes a plurality of adjacent blades arranged along the first end and extending longitudinally and perpendicularly thereto. In particular, a portion of the blades has an accordion-shaped structure.

Abstract: The invention relates to a nacelle for a turbojet engine that includes an air intake structure capable of directing an air flow towards a fan of the turbojet engine, and a middle structure for surrounding said fan and to which is attached the air intake structure in order to provide aerodynamic continuity, wherein the air intake structure includes at least one inner panel attached to the middle structure and defining, with the latter, a nacelle fixed structure and at least one outer longitudinal panel removably attached to the fixed structure and including an air intake lip in order to define a removable air intake structure, wherein the removable air intake structure is provided with a locking device including at least one electric lock capable of interaction with a complementary retention structure.

Abstract: A fire-resistant seal for a propulsion assembly which includes a pylon, an O-duct type nacelle of a turbojet engine. The nacelle includes an inner fixed nacelle structure and a combustion gas ejection primary nozzle, and the fire-resistant seal is placed in an annular sector defined by the inner fixed nacelle and the gas ejection primary nozzle. In particular, the fire-resistant seal includes a plurality of baffles, and the plurality of baffles are longitudinally disposed so as not to interfere each other during a longitudinal translational movement of the inner fixed nacelle structure relative to the combustion gas ejection primary nozzle.

Abstract: The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside.

Abstract: An air intake structure is mounted upstream of a mid-structure of a nacelle for an aircraft engine. The air intake structure includes an external wall incorporating a lip, a partition defining a deicing compartment in the lip, a deicing manifold extending in the compartment, and a duct for supplying hot air to the deicing manifold. In particular, the external wall is mounted movably with respect to the mid-structure between a rear position and a front position, and the duct is connected in a fixed manner to the mid-structure. The partition is fixed in a sealed manner inside the lip, and the duct is connected to the manifold by a disconnectable seal which is situated in an immediate vicinity of the partition.

Abstract: An air inlet structure which is mounted upstream of a central structure of a nacelle of an aircraft engine includes an outer partition incorporating a lip, an upstream partition defining with the outer partition a deicing compartment in the lip, and a hot air supply device to supply the deicing compartment with hot air. The hot air supply device has a hot air supply tube and a peripheral seal plate surrounding the supply tube. In particular, the hot air supply tube has an elbowed free end, and an orifice of the upstream partition allows passage of the elbowed free end according to a main axis of the supply tube. The seal plate includes a contact plate surrounding the supply tube to ensure sealing at the upstream partition.

Abstract: A seal assembly for a turbojet nacelle includes a first end fastened to a first structure, and a second end contacting against a bearing zone of a second structure. The seal assembly further includes a plurality of adjacent blades arranged along the first end and extending longitudinally and perpendicularly thereto. In particular, a portion of the blades has an accordion-shaped structure.

Abstract: A nacelle includes a central structure intended to surround a fan of a turbojet engine and an air intake structure attached to the central structure and able to channel a flow of air toward the fan. The nacelle includes at least one longitudinal outer panel incorporating an air intake lip. An inner panel includes an acoustic shell ring which downstream end is attached to an upstream end of the central structure and therewith forms a fixed structure of the nacelle. Guide means are entirely attached to the central structure for guiding the outer panel or panels and allowing substantially rectilinear movement of the outer panel towards the upstream end of the nacelle so that the air intake structure can be opened.

Abstract: The invention relates to a turbojet engine nacelle (1) comprising: an outer structure including an annular lip defining an air inlet and a cowl (9) extending as a continuation of the annular lip, and an inner fixed structure (19) extending as a continuation of the air inlet and including a region equipped with at least one piece of equipment requiring maintenance or monitoring. The aforementioned outer structure can move in relation to the inner structure between an operating position in which the cowl (9) covers the region equipped with the equipment and a maintenance position in which the cowl (9) reveals said region so as to allow access to the equipment from outside.

Abstract: Turbojet engine nacelle (1) comprising an air intake structure (4) able to channel a flow of air towards a fan of the turbojet engine, and a central structure (5) intended to surround said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, the central structure comprising, on the one hand, a casing intended to surround the fan and, on the other hand, an outer structure, characterized in that the air intake structure comprises a longitudinal outer panel (40) incorporating an air intake lip (4a) and which may extend so far as to incorporate at least part of the outer structure of the central section and beyond, said longitudinal outer panel being translationally mobile between an operating position in which the outer panel ensures the aerodynamic continuity of the outside of the nacelle (1), and a maintenance position in which the outer panel (40) is set away from the outer structure of the central section and the air intake lip (4a) is set away from the inn

Abstract: The invention relates to a nacelle (1) for a turbojet engine, comprising: —an air intake structure able to channel a flow of air towards a fan of the turbojet engine and comprising at least one longitudinal outer panel (40) incorporating an air intake lip (4a), —a middle structure (5) intended to surround the said fan and to which the air intake structure is attached in such a way as to ensure aerodynamic continuity, —at least one inner panel (41) comprising an acoustic shroud (53), fixed at its downstream end to an upstream end of the middle structure (5) forming therewith a fixed structure of the nacelle (1), and —means (15) of guiding the outer panel or panels (40) which means are able to allow a substantially rectilinear movement of the outer panel (40) in the upstream direction of the nacelle (1) so as to be able to open the air intake structure, the said nacelle (1) comprising reinforcing means (90) designed to react the mechanical loads of the guide means (15) beyond a predetermined deformation thereof

Abstract: The invention relates to an air intake structure capable of being mounted upstream of a central structure of a nacelle for an aircraft engine, the said air intake structure comprising: —an external wall incorporating a lip, —an upstream partition (108) defining, with the external wall, a deicing compartment (103) in the said lip and comprising an orifice, —a hot air supply device (105) intended to supply the deicing compartment (103) with hot air, the said device (105) comprising a hot air supply tube (107) and a peripheral sealing element (109) surrounding the said supply tube (107), the hot air supply tube (107) having an elbowed free end (111), the orifice (113) in the upstream partition being configured to allow the free end (111) to pass along the main axis (115) of the supply tube, and the sealing element (109) comprising a contact plate (121) surrounding the said tube (107) so as to provide sealing at the upstream partition (108).

Abstract: The invention relates to a nacelle for a turbojet engine that comprises an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and an intermediate structure for surrounding said fan and to which the air intake structure is attached in order to ensure aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the intermediate structure and defining with the latter a fixed nacelle structure and, on the other hand, at least one longitudinal outer panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to form a removable air intake structure, characterised in that the air intake structure is provided with peripheral locking means including at least one locking means (10) attached to the inner panel or to the air intake lip and each capable of interacting with an additional retaining means (11) respectively attached to the air intake lip or to the inner panel.

Abstract: The invention relates to an air intake for an aircraft nacelle that comprises a shroud (19) that can be mounted on the fan casing (15) of a turbojet engine (1). The shroud (19) is sized so as to define a circumferential gap (J) relative to the casing (15). Punctual linking means (27, 33) between the shroud (19) and the casing (15) are discretely distributed at the periphery of said shroud (19).

Abstract: The invention relates to a nacelle for a turbojet engine that includes an air intake structure (2) capable of directing an air flow towards a fan of the turbojet engine, and a middle structure for surrounding said fan and to which is attached the air intake structure in order to provide aerodynamic continuity, wherein the air intake structure includes, on the one hand, at least one inner panel (21) attached to the middle structure and defining, with the latter, a nacelle fixed structure and, on the other hand, at least one outer longitudinal panel (20) removably attached to the fixed structure and including an air intake lip (2a) in order to define a removable air intake structure, characterised in that the removable air intake structure is provided with peripheral locking means including at least one electric lock (10) each capable of interaction with a complementary retaining means (11).

Abstract: This maintenance trolley (17) for the air intake (9) of the nacelle of an aircraft turbojet engine is notable in that it comprises a base (19) and a platform (23) cantilever-mounted on this base (19) and designed to enter said air intake (9) without contact therewith.

Abstract: The present invention relates to a turbojet engine nacelle (1) comprising:—an air intake structure (4) capable of channelling an airflow towards a fan of the turbojet engine and comprising at least one longitudinal external panel (40) incorporating an air intake lip (4a),—a central structure (5) intended to surround the said fan and to which the air intake structure (4) is attached in such a way as to ensure aerodynamic continuity,—at least one internal panel (41) comprising an acoustic shelving fixed at its downstream end to an upstream end of the central structure (5) therewith forming a fixed structure of the nacelle (1), and—guide means (15) for guiding the external panel or panels (40) which are capable of allowing substantially rectilinear movement of the external panel (40) towards the upstream end of the nacelle (1) so as to be able to open up the air intake structure (4), the guide mans (15) being entirely fixed to the central structure (5).