Airbus France

Airbus Operations (s.a.s.)

Aerospatiale Societe Nationale Industrielle

Societe Nationale Industrielle Et Aerospatiale

Airbus Operations (societe Par Actions Simplifiee)

Herve Marche

Fabien Raison

Alain Porte

Jean-Marc Martinou

Gilles Weyland

An aircraft propulsion unit including a turbojet and a heat exchanger located above the turbojet and drawing a cooling air stream and a hot air stream in the turbojet. Wherein the cooling air intake and hot air intake surfaces in the housing are directed forward of the turbojet and have normal lines inclined relative to the axis of the turbojet. The embodiment also concerns an aircraft equipped with at least one such propulsion unit.

Propulsion unit for aircraft with heat exchanger having front inlet faces for cooling air flow and hot air flow

A damage-tolerance attachment system for an aircraft engine includes first and second attachment devices attaching the aircraft engine to a pylon fixedly attached to the aircraft, and a third backup attachment device including a first portion attached to the pylon and a second portion attached to the engine, the first and second portions connected together loosely so as not to disrupt an isostasy of the first and second attachment devices.

Damage-tolerant attachment system for an aircraft engine

Sail wing aircraft which includes a wing () and at least one propulsion engine (). It includes an upper beam () which is firmly fixed at its front end to a first frame () located on an air inlet () of the propulsion engine and which is in addition firmly fixed at its median part to a second frame () located to the rear of the first frame. The sail wing aircraft includes in addition a pylon () for attachment of the engine onto the fuselage, where the engine is fixed to the pylon ().

Sail wing aircraft which includes an engine mounted on a pylon

An engine unit for an aircraft including a turboprop engine and its device for mounting on to a wing surface. The device includes a rigid structure and a mechanism for fastening the turboprop engine on to this structure. The fastening mechanism includes six mutually independent hydraulic systems, each one exclusively dedicated to the transfer, to the rigid structure, of forces exerted respectively according to one of the six degrees of freedom of movement. Each hydraulic system includes at least one hydraulic jack with a piston attached to one of the two elements, i.e. either the turboprop engine or the rigid structure, together with a cylinder housing the piston and attached to the other of the two elements.

Device for mounting an aircraft turboprop engine comprising hydraulic attachments

A system for attaching an engine to the structure of an aircraft, such as a sail wing aircraft is disclosed. The system includes an upper beam which is firmly fixed at its front end to a first frame mounted on the aircraft structure, and firmly fixed at its median part to a second frame located to the rear of the first frame. The engine is hooked beneath the upper beam. The system is orientated in relation to a longitudinal axis X, a transverse axis Y and a vertical axis Z. Two front engine attachment points are arranged symmetrically on either side of the vertical median plane of the engine. The front attachment points include a shaft which is inclined relative to the Y-direction and to the Z-direction so that they bear the forces along the longitudinal direction and forces which are inclined relative to the Z-direction and Y-direction.

System for attaching an engine to the structure of an aircraft, such as a sail wing aircraft

A propulsion system for an aircraft includes a heat exchange unit through which a hot air stream and a cooling air stream flow. The heat exchange unit includes a hot air inlet pipe situated on a rear face of the heat exchange unit, to carry the hot air stream into the heat exchange unit, and a cooling air discharge pipe situated on the rear face of the heat exchange unit to expel the cooling air stream from the heat exchange unit, the hot air inlet pipe and the cooling air discharge pipe being concentric with each other. The hot air stream flows from the rear face forward to a front of the heat exchange unit, then from the front of the heat exchange unit, to a rear of the heat exchange unit, so as to be expelled via the rear face of the heat exchange unit.

Heat exchanger unit for an aircraft

A nacelle cowling for a turbojet, characterized in that it is provided with a fixed part and a mobile part, the mobile part being adapted to slide along the fixed part, from a closed position wherein the mobile part extends in the extension of the fixed part, up to an open position wherein the mobile part is at least partly superimposed to the fixed part. For example, the fixed part is located in the upper part of the cowling, the mobile part being located in the lower part of the cowling.

Nacelle cowling for turbojet and nacelle comprising at least one such cowling

A propulsion unit comprises a turbojet engine and a thermal exchanger, situated above the turbojet engine. The turbojet engine comprises a regulation device to regulate an air flow-rate in a cooling air lead-in conduit conveying a stream of cooling air into a thermal exchanger, The regulation device regulates the air flow-rate upstream with respect to the cooling air lead-in conduit.

Turbojet engine for aircraft, propulsion unit comprising such a turbojet engine and aircraft comprising such a propulsion unit

A heat exchanger comprising a main heat exchange housing, a cooling air inlet line and a hot air inlet line to bring a cooling airflow and a hot airflow in the main housing. A heat pre-exchanger is disposed upstream from the main housing, the heat pre-exchanger being able to be crossed by the cooling airflow and the hot airflow prior to the main housing. The invention also relates to a propulsion unit and an aircraft comprising such a heat exchanger.

Heat exchanger, propulsion unit, and aircraft comprising such a propulsion unit

A pod for an aircraft including a cowling, an engine housed in the inner volume of the cowling, an annular channel circulating a secondary thrust flow arranged between the engine and the cowling, and at least one thrust reverser for forming a reverse flow from the secondary thrust flow circulating in the annular channel. The thrust reverser including a plurality of doors provided in the rear part of the cowling, so as to form a trailing edge of the cowling. The thrust reverser can include means for actuating the doors such that at lease one actuating means actuates two adjacent doors and at least one door is actuated by two actuating means.

Aircraft pod and aircraft equipped with at least one such pod

This invention relates to a mounting system () inserted between an aircraft engine () and a rigid structure () of an attachment strut () fixed under a wing () of this aircraft, the system including a forward mount (), an aft mount () and a device () for resisting thrusts generated by the engine (). The system also comprises additional means () for opposing the longitudinal bending of the engine (), these additional means () being designed to resist loads only starting from a predetermined deformation of this engine (). According to the invention, the additional means () comprise at least one connecting rod () capable of opposing longitudinal bending of the engine (), each connecting rod () being connected firstly to the rigid structure () of the strut () and secondly to a fan casing () of the engine (), so that it is only stressed starting from the predetermined deformation of this engine ().

Mounting system inserted between an aircraft engine and a rigid structure of an attachment strut fixed under a wing of this aircraft

This invention relates to a mounting system () inserted between an aircraft engine and a rigid structure of a strut, comprising a thrust resistance device () comprising a spreader beam () provided with two lateral lower ends () placed such that a horizontal plane passes through them and through a longitudinal axis of the engine. Moreover, the device () is also fitted with two fittings () each comprising a forward end () through which the said horizontal plane also passes and fixed to a forward part of a central casing (), and an aft end () connected to one of the ends (). Furthermore, the spreader beam is connected to the forward mount and to the rigid structure through its upper end ().

The invention concerns a pod (16) of an aircraft motor (10) suspended from a pole (14) and comprising a pod cowling (24) joined to the pole (14) along a hinge pin (26) which forms a first angle .alpha. with a first plane (27) passing through the axis of the motor and perpendicular to a second median plane (29) of the pole. According to the invention, the hinge pin (26) forms a second angle .beta. with the median plane (29) so as to make the closing elements of the cowling (25) coincide with complementary corresponding elements of the adjacent edges (30) of the pod (16) when the cowling is closed.

Aircraft motor pod including a pivotable pod cowling

In a turbofan engine, particularly of the type in which the front end of the fan frame (26) is separate from the air inlet (24), the seal between the said two structures is provided by an elastic sleeve (32) fixed to the air inlet and fitted onto the front part of the fan frame. The diameter of the part of the sleeve before it is mounted onto the frame (26) is smaller than the external diameter of the front part of the latter. The sleeve (32) has an internal fitting preventing any relative circumferential displacement between the two ends thereof. An inflatable member (46) can be placed about that part of the sleeve which is fitted into the frame.

Growing community of inventors

Roquettes, France

Herve Marche