| Document |
Document Title |
|
WO/2011/091591A1 |
A net at the air inlet of aero plane engine is for avoiding birds to impact engine during flight. Such net will settle the problem that the jet engine may not work while the birds fly in.
|
|
WO/2011/086273A1 |
The invention relates to an aircraft nacelle comprising an air inlet (110) with a lip (114) extended to the back by a passage (116) that makes it possible to channel an air flow to a drive (112), said passage (116) comprising at least on...
|
|
WO/2011/086281A1 |
The invention relates to an aircraft nacelle including a first subassembly consisting of a pipe (112) channeling an airflow in the direction of an engine having a covering or panel (118) for acoustic treatment, including, from the inside...
|
|
WO/2011/082299A1 |
A fan containment system for a gas turbine engine, and a method of making the same, is disclosed that in one embodiment includes casing that surrounds at least a portion of a plurality of fan blades. In one form, a pair of standoff rings...
|
|
WO/2011/046580A2 |
A bird deflector and air replacement system for a jet engine, the bird deflector being conical or arcuate in shape as formed by suitable longitudinal and lateral interconnected bars, and the air replacement apparatus being one of a frust...
|
|
WO/2011/007074A1 |
The invention relates to a structure of a leading edge (1), in particular for the air intake of an aircraft nacelle, including a leading edge (2) and an inner partition wall (3) defining a longitudinal compartment (5) inside the leading ...
|
|
WO/2011/002879A2 |
A fluid check valve for use in an aircraft fluid handling system having a confined surrounding structure where a first distance is defined between a fluid duct and the surrounding structure where the design of the fluid check valve is co...
|
|
WO/2011/002886A2 |
An aircraft check valve assembly where the fluid check valve is indexed in rotational position relative to a first duct flange and to a second opposed duct flange and to a clamping band where the check valve includes an annular check val...
|
|
WO/2010/136369A1 |
The invention relates to a nacelle for receiving an aircraft engine (2), comprising a fixed tubular cowl and at least one mobile portion connected to the fixed cowl by a means for moving the mobile portion between a near position and a s...
|
|
WO/2010/119210A1 |
The invention relates to a system for actuating a plurality of actuators (15) that can move a mobile panel of an aircraft nacelle. Said system comprises at least two motors (16) that can drive the actuators (15), the two motors (16) bein...
|
|
WO/2010/109152A2 |
The invention relates to an aircraft nacelle including a wall defining an inner duct (42) that channels an airflow towards a drive means, a lip (44) in the front thereof, an outer wall (46) on the outside thereof that defines a cavity (5...
|
|
WO/2010/107802A1 |
Disclosed herein is a method for making polyimide articles that are suitable for use in an aircraft. The articles disclosed herein are rigid, oxidatively stable, wear-resistant, and permeable to heated moisture and gases, and comprise co...
|
|
WO/2010/089496A1 |
The invention relates to an acoustic processing panel mounted at the air intake of an aircraft nacelle, said panel including at least one acoustically resistive structure (30) and a reflective layer (32), between which are provided, in a...
|
|
WO/2010/089498A2 |
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) extendi...
|
|
WO/2010/089497A1 |
The invention relates to a method for making an acoustic processing panel, comprising an acoustically resistive porous layer (12), at least one cellular structure (14), a reflective structure (16) with openings, and a drainage plate (22)...
|
|
WO/2010/086560A2 |
The invention relates to an aircraft nacelle including a duct (32), a peripheral wall (34), a lip (36) and a front frame (38) connecting the peripheral wall (34) and the duct (32) and defining a gap (50) with the lip (36) in which hot ai...
|
|
WO/2010/077241A1 |
A filtration system for a gas turbine engine includes an inlet main body which defines an inner inlet fairing section and a bellmouth inlet faring section transverse thereto. An Engine Air Particle Separator (EAPS) is mounted adjacent to...
|
|
WO/2010/055224A1 |
Air intake (113) for an aeroplane engine of the type with unducted propellers, which intake is intended to be connected by a pylon (134) to the fuselage of an aeroplane, the local length of this air intake, measured parallel to the axis ...
|
|
WO/2010/040907A1 |
The invention relates to an air intake structure (4) for a turbine engine nacelle for directing an air flow towards the fan of the turbine engine, said structure comprising at least one outer panel (40), at least one inner panel (41) and...
|
|
WO/2010/040911A1 |
The invention relates to an arrangement (1) that comprises a mobile plate (18) controlled by a means for fluid communication (23) between the outer (18A) and inner surfaces of the mobile plate (18), wherein said means is located at least...
|
|
WO/2010/040837A2 |
The invention relates to a sound absorber (2) for an auxiliary engine of an aircraft comprising an inlet (46), an outlet (48), a housing (4), and a flow channel (6) which has a porous wall material and is arranged in the housing (4). An ...
|
|
WO/2010/034893A1 |
The invention relates to a nacelle that comprises a fixed structure (20), a nozzle with a variable section, and a cowling (30) mounted on said fixed structure (20) so as to be capable of sliding particularly along a travel so as to modif...
|
|
WO/2010/034922A1 |
The invention relates to an aircraft nacelle comprising an air inlet (50) enabling air to be channeled into a duct (54) in the direction of a duct (56) of an actuator assembly (52) forming an extension of said duct (54), said air inlet d...
|
|
WO/2010/022362A2 |
A first trailing edge portion (26) of a scarfed jet engine exhaust nozzle (24) aft of a second trailing edge portion (30) relative to a central axis (16) of an associated exhaust duct (10, 10.1) causes an automatic nozzle-pressure-ratio ...
|
|
WO/2010/018314A1 |
The invention relates to an inner wall for the nacelle of a turbine engine that comprises an outer annular fan casing (126) surrounding fan blades and having an upstream flange (130) for attachment onto a coaxial ring (134), and a soundp...
|
|
WO/2010/015758A1 |
The invention relates to a method for making a deicing system on a panel (22) of a nacelle comprising an outer skin (24) having at least one hole and an inner skin (26), characterized in that it comprises the following steps: A. a grid o...
|
|
WO/2010/012899A2 |
This assembly comprises a first component (9), a second component (3), and a connecting device (19) for connecting these two components together, this device (19) being of the type that maintains the integrity of the surface of said seco...
|
|
WO/2010/007258A1 |
This aircraft engine nacelle air intake assembly comprises an air intake structure comprising an air intake lip (7) and an acoustic shroud (5) extending downstream of this air intake lip (7) and designed to be mounted on a fixed structur...
|
|
WO/2010/001009A2 |
The subject of the invention is an aircraft nacelle comprising an air intake (40) able to channel an airstream (42) towards a drive unit (44), the said air intake (40) comprising an interior duct (48) forming an aerodynamic surface (52) ...
|
|
WO/2010/001008A1 |
The subject of the invention is a method of depositing a coating for improving laminar flow at a joint between a first panel (36) of a leading edge and a second panel (34) of a surface which is adjacent in the direction of said flow, cha...
|
|
WO/2010/000953A1 |
The present invention relates to a nacelle for a turbojet engine comprising an air intake structure able to channel an airflow towards a fan of the turbojet engine, and a middle structure comprising a casing (9) intended to surround the ...
|
|
WO/2009/157780A1 |
A personal flight device which includes: a housing which is securable to a pilot; at least one pair of ducted fans, one fan of the pair mounted to one side of the housing, the other fan of the pair mounted to the other side of the housin...
|
|
WO/2009/142793A2 |
A leading edge structure for use in an aerospace vehicle includes a body (38) having a flowpath surface (48) which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented i...
|
|
WO/2009/138685A2 |
The invention relates to an aircraft nacelle comprising: an air inlet (40) enabling the channeling of an air flow (42) in the direction of a motor (44), said air inlet (40) comprising an inner duct (48) forming an aerodynamic surface (52...
|
|
WO/2009/135260A1 |
A fluid dynamic device (100) for directing fluid flow to generate thrust comprising a thrust control shroud (130) disposed about a central axis (210) of said fluid dynamic device (100) for directing a fluid flow between an upstream fluid...
|
|
WO/2009/136096A2 |
The invention relates to a bypass turbojet engine nacelle comprising a downstream section equipped with a thrust reverser device comprising a moving cowl (6) mounted such that it can move in translation in a direction substantially paral...
|
|
WO/2009/136062A2 |
The subject of the invention is an acoustic treatment panel comprising, beginning on the inside and working outwards, a reflective layer (50), at least one honeycomb structure (52), and at least one acoustically resistive structure (54) ...
|
|
WO/2009/125157A2 |
The invention relates to a turbofan engine nacelle (1) comprising at least one cowling structure (8, 9) having an internal wall (10) intended to define an external wall of an annular duct (6) in which a secondary stream (F) flows, said s...
|
|
WO/2009/122037A2 |
According to the invention, fresh air (E) at the turboprop outlet is captured and mixed with the warm airflow (F) created by said turboprop to lower the temperature.
|
|
WO/2009/122066A2 |
The invention relates to a lip that includes, on the inner surface thereof, an electric de-icing device (11) comprising at least one panel including a cellular structure (13), made of electrically conductive material, and an electrical c...
|
|
WO/2009/118470A1 |
The invention relates to a device for supporting and securing a piece of equipment (10) on an aircraft engine or nacelle case (12), including a vibration damper (16) having a first part secured to the case and a second coaxial part rigid...
|
|
WO/2009/115674A2 |
The invention relates to an air intake for an aircraft nacelle that includes a fixed shell (1) and a cowling (7) comprising an outer wall (9) and an air intake lip (10) arranged as an extension of said outer wall and defining an annular ...
|
|
WO/2009/112695A1 |
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 upstrea...
|
|
WO/2009/109712A1 |
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 ...
|
|
WO/2009/108672A2 |
This invention relates to a honeycomb core having improved shear properties made from a p-aramid paper substrate. The paper comprises 50-85 parts by weight of p-aramid floc, 10-40 parts by weight of p-aramid pulp and 5-30 parts by weight...
|
|
WO/2009/098044A1 |
Engine inlet flap (K) for mounting on the housing of an air inlet or air inlet duct of an engine of an aircraft, having a first end (E1) and a second end (E2) arranged in opposition thereto at a distance therefrom in the longitudinal dir...
|
|
WO/2009/095257A2 |
Wing-propulsion unit combination comprising a wing (W) with a main wing (W1) and a propulsion unit (E) with a pre-mix chamber (E1), a combustion chamber and a hot air chamber (E2), further comprising: a) a propulsion unit tap air channel...
|
|
WO/2009/083074A1 |
The invention relates to a device (2) for cooling hot gas that is to be discharged from an aircraft. Said device (2) comprises a duct (6, 8, 10) for conducting the hot gas from a hot gas source that can be connected to the device to a di...
|
|
WO/2009/083691A1 |
The subject of the invention is an aircraft propulsion assembly comprising a nacelle (50) in which there is a power plant (52), the said nacelle comprising an interior wall delimiting a duct (54) with an air inlet (56) at the front, the ...
|
|
WO/2009/085843A2 |
An aircraft component (200) includes a first segment (110) having a first leading edge surface that extends to a first end (222) of the first segment. The aircraft component also includes a second segment (112) having a second leading ed...
|
