A thrust reverser of a nacelle may include a translating sleeve and an inner fixed structure a pressure relief assembly. A pressure relief mechanism may include a pressure relief door coupled via a hinge and a latch to the inner fixed structure. Alternatively, a pressure relief door may be coupled to a frame via a hinge and a latch to the inner fixed structure. The pressure relief assembly may limit deflections between the thrust reverser and the pylon in response to a burst duct. The pressure relief door may release from the latch automatically in response to an over pressurization event.

A propulsion system comprising a nacelle with an air channel along a longitudinal direction, an electric motor whose output drives a propeller, and a fuel cell, comprising a core outside the air channel, open channels, each of which has an inlet and an outlet opening in the air channel, and, for each open channel, a fuel chamber, an electrolyte between the open channel and the fuel chamber, a cathode, and an anode, each open channel having an inlet surface area which is less than the surface area of an intermediate area between the inlet and the outlet, the surface area of the outlet being smaller than the surface area of the intermediate area. Such a system makes it possible to have the fuel cell close to the electric motor, thereby reducing the lengths of the electrical conductors between them, and consequently improving the operation of the fuel cell.

The disclosure relates to a modular arrangement of a converter for the electrical supply of a multi-phase electric motor. The modular arrangement includes multiple output stage modules, each module having a separate first housing. An output stage module is provided for each phase of the electric motor, wherein the output stage module has a phase intermediate circuit and an inverter circuit, together forming a commutation cell. The phase intermediate circuit supplies DC voltage and is electrically connected to the inverter circuit. The disclosure also relates to a motor arrangement and an aircraft having a motor arrangement of this type.

The disclosure relates to a modular arrangement of a converter for the electrical supply of a multi-phase electric motor. The modular arrangement includes multiple output stage modules, each module having a separate first housing. An output stage module is provided for each phase of the electric motor, wherein the output stage module has a phase intermediate circuit and an inverter circuit, together forming a commutation cell. The phase intermediate circuit supplies DC voltage and is electrically connected to the inverter circuit. The disclosure also relates to a motor arrangement and an aircraft having a motor arrangement of this type.

An aircraft includes a battery pack, an internal support structure to support the battery pack in the aircraft, a first bracket rigidly coupling the battery pack to the support structure, and a second bracket rotationally coupling the battery pack to the support structure. The first and second brackets may be located on opposite sides of the battery pack. The internal support structure may be located in a wing of the aircraft and the first and second brackets may be aligned in a fore-aft direction of the aircraft. The internal support structure may be located in a nacelle of the aircraft and the first and second brackets may be aligned along a transverse direction of the aircraft. The second bracket may include two hangers to support a mass of the battery pack in tension.

An aircraft includes a battery pack, an internal support structure to support the battery pack in the aircraft, a first bracket rigidly coupling the battery pack to the support structure, and a second bracket rotationally coupling the battery pack to the support structure. The first and second brackets may be located on opposite sides of the battery pack. The internal support structure may be located in a wing of the aircraft and the first and second brackets may be aligned in a fore-aft direction of the aircraft. The internal support structure may be located in a nacelle of the aircraft and the first and second brackets may be aligned along a transverse direction of the aircraft. The second bracket may include two hangers to support a mass of the battery pack in tension.

In accordance with at least one aspect of this disclosure, there is provided a system for an aircraft engine. In embodiments, the system includes an accessory box and a fuel accessory located in an interior space within the accessory box, where a vent is defined through a wall of the accessory box. In embodiments, the vent includes a plurality of holes or slots in an outer wall of the accessory box for passage of gaseous fuel from the interior space. In embodiments, the vent is configured for passive ventilation of the interior space.

A surface liner member includes an external wall which is provided with multiple holes, a spacer structure, and tubes which are respectively associated with the holes in the external wall. The surface liner member is intended to be applied to a base surface in order to reduce, by acoustic absorption, an acoustic wave reflected on this base surface. The acoustic absorption efficiency is improved, particularly for frequencies below 500 Hz, by varying the shape of the holes in the external wall such that the ratio of the hole perimeter to the hole area varies. Such a surface liner member may be adapted to form a surface portion of an aircraft engine nacelle, or of a leading edge of an aircraft wing.

A surface liner member includes an external wall which is provided with multiple holes, a spacer structure, and tubes which are respectively associated with the holes in the external wall. The surface liner member is intended to be applied to a base surface in order to reduce, by acoustic absorption, an acoustic wave reflected on this base surface. The acoustic absorption efficiency is improved, particularly for frequencies below 500 Hz, by varying the shape of the holes in the external wall such that the ratio of the hole perimeter to the hole area varies. Such a surface liner member may be adapted to form a surface portion of an aircraft engine nacelle, or of a leading edge of an aircraft wing.

A front fan turbomachine includes an annular separating wall having a slat for separating an air flow between a primary flow and a secondary flow, the slat having a leading edge; inlet guide vanes (IGV) for guiding the primary flow and outlet guide vanes (OGV) blades for guiding the secondary flow. The leading edge of the slat has a serrated profile having a succession of teeth and depressions.