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WO/2015/080785A2 |
A cascade set for creating sufficient drag to slow an aircraft is disclosed. The cascade set includes one or more supporting vanes. A plurality of turning vanes are connected to the supporting vanes, and the turning vanes include forward...
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WO/2015/071609A1 |
The invention relates to a de-icing device comprising a piccolo tube (43) built into the front wall (37) defining the inner volume of the perforated front lip (36). The piccolo tube (43) is in contact with an alveolar noise-reduction str...
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WO/2015/067565A1 |
Methods and apparatus for producing a heat exchanger (4), the method comprising: producing a digital model (76) of the heat exchanger (4) by: producing digital model of a first conduit (10) having a first end portion (26) and an opposite...
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WO/2015/059489A1 |
An anti-icing system (303) can be provided within a chamber (212) having an exterior wall (210) of which an outer surface (301) can be subject to ice formation. The anti-icing system comprises a nozzle (213) arranged to inject hot gas wi...
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WO/2015/052457A1 |
The invention concerns a nacelle (10) for an aircraft engine, comprising a thrust reverser cowling (20) that is slidably mounted between a direct jet position, and a reversed jet position in which the cowling (20) opens a passage in the ...
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WO/2015/041855A1 |
The present disclosure relates to shock mounts for turbine engine components. A shock mount (46) may be used to mount an accessory gearbox (40) to an engine case (22). The shock mount may allow free thermal expansion, while providing dam...
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WO/2015/034513A1 |
An aircraft including a jet engine including a core having a compressor and combustion chamber, and a particulate sensor located within the core and a particulate detection method for an aircraft having a jet engine where the method incl...
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WO/2015/028757A1 |
The invention relates to a production method and a honeycomb composite panel according to which two honeycomb structures (5, 6) are assembled along one of the connecting edges of said structures above a step (22) in a skin of variable th...
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WO/2015/022460A1 |
Assembly comprising a shell ring (2) equipped with a flange (30), this shell ring having a substantially axial part that receives with a tight fit, on the inside or the outside, a complementary axial part of the flange that is fixed by a...
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WO/2015/015128A1 |
A piece of electronic equipment (18) of a turbomachine (10), comprising a wall (28) of which the inner surface defines at least one channel (26) for the passage of a ventilating air stream of which the outlet (32) opens on an outer surfa...
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WO/2015/001276A1 |
The present invention relates to a turbofan nacelle having a downstream section including at least one cowling (3a) ending in at least one hinged flap (50) constituting a nozzle, characterised in that said flap is hingedly and translatab...
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WO/2014/207236A1 |
The invention relates to an aircraft structure (10), in particular the fuselage, nacelles or wings, comprising, over all or part of an outer surface (21) that may undergo lightning impacts, a layer of flexible polymer (30), a photovoltai...
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WO/2014/207408A1 |
The invention concerns device for de-icing an air inlet lip (111) of an aircraft nacelle (100), said device comprising a pre-exchanger (2), an intake means capable of taking in low-pressure air downstream from the fan (12), two high-pres...
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WO/2014/202881A1 |
The invention relates to a jet pump type ejector (36) for a turbomachine, including a duct (40) through which a secondary ventilation air flow passes, and a first end of which forms an air intake (42) and a second end of which forms an a...
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WO/2014/202874A1 |
The invention relates to an accessory gearbox (10) for a turbomachine, said gearbox being equipped with an air/oil separator (12) and comprising a casing (24) in which intermeshing pinions are mounted, one (18) of which is solidly connec...
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WO/2014/198923A1 |
The invention relates to an electric propulsion assembly for an aircraft, including a nacelle (10) comprising a nacelle cover (10) which defines an inner space in which an electric propulsion unit, which includes a blower (13), of the ai...
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WO/2014/200590A2 |
An inlet protection system for filtering air prior to entry into an air intake of an engine of an aircraft includes interchangeably a particle separator panel and a barrier filter panel. The barrier filter panel is adapted to be mounted ...
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WO/2014/197033A2 |
A geared turbofan engine includes a fan, a low pressure turbine, a geared architecture, and a nacelle. The fan and low pressure turbine are capable of rotation about an axial centerline of the gas turbine engine. The geared architecture ...
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WO/2014/171849A1 |
The claimed invention is related to aviation and, in particular, to supersonic passenger aircraft. In one variant embodiment, the claimed invention has a wing, a fuselage, and two turbojet engines provided at the tail part of the fuselag...
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WO/2014/170609A1 |
A nacelle for an aircraft turbojet engine with an extended front lip. The nacelle for an aircraft turbojet engine comprises an upstream partition (2) and a downstream partition (6) linking a substantially cylindrical inner envelope (11) ...
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WO/2014/163724A2 |
A wing including a spar, a box shaped sleeve in the spar running substantially the entire length of the wing, a skin affixed to spar and to the corners of the sleeve and shaped to from a leading edge and trailing edge of the wing, a spoi...
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WO/2014/164238A1 |
A method of actuating a hydraulic latch and a fan duct includes providing a pressurized fluid for actuating a latch, providing a valve to control flow of pressurized fluid to the latch and the fan duct, and selectively opening the valve,...
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WO/2014/158247A1 |
A flight vehicle (10) includes a fuselage (12) and a gas turbine engine (14). The gas turbine engine is coupled to the fuselage to provide thrust when air surrounding the flight vehicle is admitted to the gas turbine engine and combusted...
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WO/2014/151275A1 |
A nacelle for a gas turbine engine includes a upper and lower bifurcations, an inner diameter cowl and a first latch system. The inner diameter cowl extends between the upper and lower bifurcations and the first latch system is mounted o...
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WO/2014/150500A1 |
A nacelle (12) for a gas turbine engine (10) that extends along an engine centerline (CL) includes an inner portion (28), an outer portion (30), and a nacelle flow control system (26). The outer portion (30) surrounds the inner portion (...
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WO/2014/143264A1 |
A total air temperature (TAT) sensor assembly is disclosed. The assembly includes a housing that accommodates a temperature sensor. The assembly also includes a first airfoil that includes a leading end and a trailing end and a second ai...
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WO/2014/135844A1 |
A heat exchanger assembly (201) comprises: a hot fluid flow channel (210); a cold fluid flow channel (220); and a heat exchanger (230) disposed between the channels. The heat exchanger comprises a heat sink (240) and a thermoelectric dev...
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WO/2014/127213A1 |
A method is provided for determining a minimum volume of headroom to leave in a package to sufficiently limit bricking of the package. It includes: determining, for a mass of contents packed in a first interior space of the package disti...
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WO/2014/122369A1 |
- According to the invention, said space aircraft comprises, at the front of each of the air inlets (5) of the turbo engines (4), a mobile flap (6) that can move, in both directions, between a first position for which said flap opens sai...
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WO/2014/118455A1 |
The invention concerns a structure (3) for feeding air to an auxiliary power unit (2) of an aircraft (1) comprising a pressurized cabin (10) and an auxiliary power unit (2), the structure comprising: a pipe (30) for feeding air to the au...
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WO/2014/114868A1 |
The subject of the invention is a seal interposed between two surfaces (60, 62) of an aircraft propulsion assembly. According to the invention, said seal comprises at least two layers, each one comprising a plurality of strands (68) made...
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WO/2014/114282A1 |
The engine for an aircraft has an engine housing comprising a turbine. A protective device or protective hood provided with a plurality of cavities is arranged in the region of an inlet of the engine housing.
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WO/2014/113444A2 |
A supplemental thrust system for an airplane comprising a submerged inlet duct, a diffuser section in communication with the inlet duct, and a duct outlet in communication with the diffuser section, an outlet nozzle in communication with...
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WO/2014/108125A1 |
The invention relates to an aircraft, wherein at least one rotatably mounted, bladed rotor (R) for generating propulsion surrounds a fuselage arrangement (F)and is arranged relative to the components of the aircraft in a defined manner a...
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WO/2014/106725A1 |
The invention relates to an electric de-icing/anti-icing device for a turbojet engine/turbo-prop nacelle element for an element of an aircraft to be protected from ice, comprising: - a heating assembly comprising two heating stages posit...
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WO/2014/102682A1 |
The nacelle (N) is provided with a built-in system (10) for anti-icing protection and acoustic absorption and comprises a casing or cowling (C), which has a substantially tubular shape and comprises an outer barrel (OB) and an inner barr...
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WO/2014/099182A1 |
According to one embodiment of the present disclosure, an exhaust apparatus for an auxiliary power unit is disclosed. The exhaust apparatus may include an exhaust housing including a perforated body surrounding an exhaust airflow of the ...
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WO/2014/092757A1 |
An aircraft includes a propulsion supported within an aft portion of a fuselage A thrust reverser is mounted in the aft portion of the fuselage proximate the propulsion system for directing thrust in a direction to slow the aircraft. The...
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WO/2013/166419A9 |
A mounting system for a fire detection system (208, 210, 400) for a turbofan engine propulsion system is provided to mount fire detection sensors (404, 500) on the inner fixed structure (IFS) of the nacelle (100). The mounting system mou...
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WO/2014/077922A2 |
A scoop inlet for use in a gas turbine engine nacelle has a scoop inlet, and a tab extending forwardly of the scoop inlet. The scoop communicates with a downstream flowpath. The tab has at least one opening at a location upstream of the ...
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WO/2014/074143A1 |
An aircraft includes a propulsor supported within an aft portion of the fuselage. A thrust reverser is supported proximate the propulsor for redirecting thrust forward to slow the aircraft upon landing. A tail extending from the aft port...
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WO/2014/072615A1 |
The invention relates to an aircraft propelled by a turbojet engine (10) with contrarotating fans, the turbojet engine being incorporated into the rear of a fuselage (2) of the aircraft in the continuation thereof and comprising two gas ...
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WO/2014/074144A1 |
An aircraft includes a fuselage including a propulsion system supported within an aft portion. A thrust reverser is mounted proximate to the propulsion system for directing thrust in a direction to slow the aircraft. The thrust reverser ...
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WO/2014/068261A1 |
Turbomachine casing (10) comprising a substantially cylindrical wall (12) and an annular one-piece acousting insulation panel (18, 20) mounted inside the wall, the panel comprising an annular surface that is radially external facing a ra...
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WO/2014/052061A1 |
An example thrust reverser of a gas turbine engine is configured to connect to an aircraft wing via a pylon via one or more thrust reverser mounts located adjacent to a top circumferential apex of the engine according to an exemplary asp...
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WO/2014/041297A1 |
A method for mounting an acoustic panel on the inner surface of an annular housing of an axial turbomachine, the cylindrical acoustic panel comprising at least one longitudinal slot so as to define two opposing ends (5A, 5B), the method ...
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WO/2014/042857A2 |
An acoustic-attenuating wall panel for a nacelle of a turbine engine may include a radiused portion. The radiused portion may include an airflow surface having a concave configuration and which may be exposed to an airflow passing throug...
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WO/2014/037650A1 |
The invention relates to an accessory drive gearbox for an aircraft turbine engine, said gearbox (140) comprising a box (42), a linkage (115) for controlling flaps of the aircraft, which linkage is designed to slide axially inside said g...
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WO/2014/020267A1 |
Helicopter engine air intake provided with an anti-icing grating that offers significant bypass flow in the event of icing. According to the invention, this air intake comprises air intake lips (30, 32), and an anti-icing grating (36) mo...
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WO/2014/014072A1 |
A helicopter (10) is provided with a mast (14), a main rotor (16), an engine (32), a radiator (34) and a body cover (24). The engine (32) and the radiator (34) are housed in the body cover (24). The body cover (24) comprises an opening (...
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