| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Streamlined profile reducing the speed deficit in its wake | US13454469 | 2012-04-24 | US08596574B2 | 2013-12-03 | Damien Prat; Camil Negulescu; Frederic Barrois; Bastien Caruelle |
| A streamlined profile reducing the speed deficit in a wake, a pylon with such a profile, a propulsion assembly including such a pylon and an aircraft including this assembly. The profile has a device for suction of air from the boundary layer formed on this profile. This suctioned air is discharged with the aid of a nozzle the outlet of which is situated close to the trailing edge of the profile. Suction of the air and discharge thereof contribute to reducing the speed deficit downstream from the profile and therefore to reducing the turbulences in this zone. | ||||||
| 122 | Attachment pylon for aircraft turboshaft engine, comprising rear flaps with mobile incidence | US13078460 | 2011-04-01 | US08579230B2 | 2013-11-12 | Lionel Diochon; Steve Bedoin; Damien Prat |
| An aircraft engine assembly including a turboshaft engine with a propeller and an attachment pylon intended to be laterally attached on a rear portion of the structure of the aircraft is disclosed. The pylon has an outer surface forming an aerodynamic profile incorporating a trailing edge which is arranged upstream of the propeller of the turboshaft engine. The pylon includes a mobile rear flap at least partially defining the trailing edge and a controller which steers the incidence of the flap according to a law depending on the incidence of the aircraft. | ||||||
| 123 | Rear part of an aircraft including an engine support structure assembled so as to oscillate on the fuselage | US13257628 | 2010-03-29 | US08480025B2 | 2013-07-09 | Laurent Lafont; Jean-Michel Saucray; Esteban Quiroz-Hernandez; Jerome Antypas; Mathieu Bonnet; Frederic Journade |
| A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings. | ||||||
| 124 | Attachment pylon for an aircraft turbo-shaft engine with concentric hot air channels | US12892374 | 2010-09-28 | US08459588B2 | 2013-06-11 | Lionel Diochon; Yann Murer |
| A pylon for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge, as well as a first hot air distribution channel passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel belonging to a system for supplying pressurized air to the aircraft. The second channel is housed inside the first channel. | ||||||
| 125 | Rear part of an aircraft comprising a structure for supporting engines, extending through the fuselage and connected thereto by at least one connecting rod | US13063302 | 2009-09-16 | US08366040B2 | 2013-02-05 | Laurent Lafont; Frederic Journade; Delphine Jalbert; Etienne Bardou |
| A rear part of an aircraft including a support structure for supporting engines, extending through the fuselage, through a first opening and a second opening. A connection structure connects the support structure to the fuselage, including a first connection mechanism connecting the support structure to a first casing forming the first opening and a second connection mechanism connecting the support structure to a second casing forming the second opening. The connection structure also includes at least one effort recovery connecting rod, the first end of which is mounted on the support structure and the opposite end is mounted on the fuselage, at a distance from the first and second openings. | ||||||
| 126 | Boundary layer energiser | US12883566 | 2010-09-16 | US08348199B2 | 2013-01-08 | Christopher T. J. Sheaf; Zahid M. Hussain |
| A boundary layer energizer (20) for energizing a boundary layer flow (33) over a surface (22), the boundary layer energizer (20) comprising one or more passages (24) terminating in one or more respective holes (26) provided on the surface (22), wherein the one or more passages (24) comprises at least one fin (25) configured so as to generate a vortex flow in the one or more passages (24) such that, when in use, a fluid emanating from the one or more passages (24) flows in a vortex. | ||||||
| 127 | Gas turbine aircraft engines and operation thereof | US12877493 | 2010-09-08 | US08297038B2 | 2012-10-30 | Richard G. Stretton |
| An aircraft propulsion arrangement including a gas turbine aircraft engine having a compressor, an oil system configured to route engine oil through a heat exchanger mounted to an external surface of an aircraft component so as to define part of an aerodynamic surface to a flow of ambient air, and a duct arrangement fluidly connecting the compressor to the heat exchanger. A method of operating the gas turbine aircraft engine, the method involving the steps of: (a) flowing engine oil through the heat exchanger and thus into heat-exchange relationship with the ambient air; and (b) directing a bleed flow of compressor gas drawn from the compressor along the duct arrangement and into heat-exchange relationship with the engine oil in the heat exchanger, wherein the directing step (b) is performed selectively. | ||||||
| 128 | Inverted Airfoil Pylon For An Aircraft | US13346614 | 2012-01-09 | US20120119019A1 | 2012-05-17 | Clark M. Butler; Ian J. Gilchrist |
| An aircraft including a wing and a pylon, wherein the pylon provides an airfoil inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series LEARJET® is provided. The improvement includes an increased distance between a leading edge of a wing and an intake of an engine of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamics of the aircraft. The method includes steps of removing an original engine from an original pylon, removing the original pylon from the fuselage of the aircraft, and mounting a new pylon in a new location adjacent to the fuselage, wherein the new location is aft of the original location. | ||||||
| 129 | REAR PART OF AN AIRCRAFT INCLUDING AN ENGINE SUPPORT STRUCTURE ASSEMBLED SO AS TO OSCILLATE ON THE FUSELAGE | US13257628 | 2010-03-29 | US20120006937A1 | 2012-01-12 | Laurent Lafont; Jean-Michel Saucray; Esteban Quiroz-Hernandez; Jerome Antypas; Mathieu Bonnet; Frederic Journade |
| A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings. | ||||||
| 130 | Inverted airfoil pylon for an aircraft | US12789306 | 2010-05-27 | US08091824B2 | 2012-01-10 | Clark M. Butler; Ian J. Gilchrist |
| An aircraft including a wing and a pylon, wherein the pylon provides an airfoil inverted for an airfoil of the wing, and an improvement and method for improved flight dynamics for 20 and 30 Series LEARJET® is provided. The improvement includes an increased distance between a leading edge of a wing and an intake of an engine of the aircraft, which reduces drag and increases lift for improved flight dynamics of the aircraft. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamics of the aircraft. The method includes steps of removing an original engine from an original pylon, removing the original pylon from the fuselage of the aircraft, and mounting a new pylon in a new location adjacent to the fuselage, wherein the new location is aft of the original location. | ||||||
| 131 | ATTACHMENT PYLON FOR AIRCRAFT TURBOSHAFT ENGINE, COMPRISING A REAR FLAP WITH MOBILE INCIDENCE | US13078460 | 2011-04-01 | US20110248116A1 | 2011-10-13 | Lionel DIOCHON; Steve BEDOIN; Damien PRAT |
| The invention relates to an aircraft engine assembly, comprising a turboshaft engine with a propeller as well as an attachment pylon (14) intended to be laterally attached on a rear portion of the structure of the aircraft, the pylon having an outer surface (20) forming an aerodynamic profile incorporating a trailing edge (21), the latter being arranged upstream of the propeller of the turboshaft engine. According to the invention, the pylon comprises a mobile rear flap (24) at least partially defining the trailing edge (21), as well as a control means (34) of the flap designed to steer the incidence of the latter, according to a law depending on the incidence of the aircraft. | ||||||
| 132 | Aircraft engine with optimized oil heat exchanger | US13039795 | 2011-03-03 | US20110215172A1 | 2011-09-08 | Predrag TODOROVIC |
| This invention relates town ejector nozzle tube 1, having along its length an essentially constant, essentially oval hollow cross-section, with an inflow lip 2, having a pitch-circle type cross-section, being arranged at a flow leading-edge area of the ejector nozzle tube 1. The inflow lip 2 is provided with a plurality of grooves 3 issuing (4) to the top and bottom sides of the ejector nozzle tube 1 and connecting to an interior 5 of the ejector nozzle tube 1 formed by the hollow profile. It also relates to an aircraft engine with optimized oil heat exchanger with at least one oil cooler 6 disposed in a trailing-edge area 7 of an aerofoil-type structure 8, with at least one flow entrance area 9 being provided to supply ambient air to the oil cooler 6 disposed in a flow duct 10, and with an ejector nozzle tube 1 in accordance with one of the claims 1 to 3 being arranged downstream of the oil cooler 6 in the flow duct 10. | ||||||
| 133 | AIRPLANE HAVING ENGINES PARTIALLY ENCASED IN THE FUSELAGE | US13061634 | 2009-10-28 | US20110163207A1 | 2011-07-07 | Philippe Gerard Chanez; Jean-Loic Herve Lecordix; Stephane Jacques Francois Thomas |
| An airplane provided with dual-flow turbojet engines having nacelles at least partially encased in the fuselage, wherein the air intake of each engine is connected to the fuselage by two boundary layer guiding walls, the walls extending towards the upstream side of the air intake and being spaced apart towards the upstream side. | ||||||
| 134 | ATTACHMENT PYLON FOR AN AIRCRAFT TURBO-SHAFT ENGINE WITH CONCENTRIC HOT AIR CHANNELS | US12892374 | 2010-09-28 | US20110108662A1 | 2011-05-12 | Lionel Diochon; Yann Murer |
| The invention relates to a pylon (14) for attaching a turbo-shaft aircraft engine designed to be laterally offset on a rear part of the aircraft structure, where the pylon possesses an aerodynamic profile which includes a leading edge (16), as well as a first hot air distribution channel (30) passing along the leading edge in order to provide anti-icing, where this engine attachment pylon includes moreover a second hot air channel (36) belonging to a system for supplying pressurised air to the aircraft.According to the invention the second channel (36) is housed inside the first channel (30). | ||||||
| 135 | BOUNDARY LAYER ENERGISER | US12883553 | 2010-09-16 | US20110103969A1 | 2011-05-05 | Christopher T. J. SHEAF; Zahid M. Hussain |
| A boundary layer energiser (20) for energising a boundary layer flow over a surface (22), the boundary layer energiser (20) comprising a plurality of passages (24), each passage terminating in a respective hole (26) provided on the surface (22), the holes being arranged in a cluster (23) on the surface, wherein the plurality of passages are angled with respect to one another at the surface such that, when in use, a vortex (24) is formed by a fluid flowing through the plurality of passages. | ||||||
| 136 | BOUNDARY LAYER ENERGISER | US12883566 | 2010-09-16 | US20110100475A1 | 2011-05-05 | Christopher T. J. SHEAF; Zahid M. Hussain |
| A boundary layer energiser (20) for energising a boundary layer flow (33) over a surface (22), the boundary layer energiser (20) comprising one or more passages (24) terminating in one or more respective holes (26) provided on the surface (22), wherein the one or more passages (24) comprises at least one fin (25) configured so as to generate a vortex flow in the one or more passages (24) such that, when in use, a fluid emanating from the one or more passages (24) flows in a vortex. | ||||||
| 137 | Supersonic aircraft jet engine installation | US12807142 | 2010-08-30 | US20110062290A1 | 2011-03-17 | James D. Chase; German Andres Garzon |
| Jet engine inlet structure of a supersonic aircraft comprising the structure having an inlet ramp and an cowl lip spaced outwardly of the ramp so that entering air flows between the ramp and lip, the lip and ramp configured to produce a first oblique shock that extends outwardly from a forward portion of the ramp to pass ahead of the lip, and a terminal shock that extends outwardly from a rearward portion of the ramp to one of the following xo) a region just ahead of the lip x1) substantially to said lip. A non-uniform shock system is created that generates a central region of nearly isentropic compression and relatively ram recovery and an outer region of reduced ram recovery but entailing reduced cowl angle and drag. Translating cowl structure and also nozzle integration with the fuselage contour to reduce boat tail drag are also provided. | ||||||
| 138 | DEVICE FOR REDUCING AERODYNAMIC DRAG | US12745022 | 2008-11-21 | US20110024572A1 | 2011-02-03 | Gerald Raymond; Philippe Bourdieu |
| A device for reducing the aerodynamic drag of a vehicle includes at least one masking element for at least one part of a nozzle of the vehicle's engine, the masking element having a resorbable material designed to be eliminated in the nozzle's flow once the engine is ignited. A space craft includes the nozzle attached to the fuselage of the space craft. | ||||||
| 139 | Aircraft having a pivotable powerplant | US11451216 | 2006-06-12 | US07766275B2 | 2010-08-03 | Arthur V. Hawley |
| Aircraft including an airframe having a fuselage extending between a forward end and an aft end opposite the forward end. The aircraft further includes a powerplant pivotally connected to the fuselage adjacent the aft end. The powerplant produces exhaust during operation of the aircraft. The powerplant is selectively pivotable to direct exhaust at multiple angles with respect to the fuselage. | ||||||
| 140 | Aircraft having a reduced acoustic signature | US12178704 | 2008-07-24 | US20090084889A1 | 2009-04-02 | Olivier Cazals; Alexander Koch |
| An aircraft the propulsive units of which include engines, and which is distinguished by reduced noise emissions, includes a wing structure fixed to an upper region of the fuselage, and a vertical tail system having at least two vertical stabilizers which are generally vertically fixed to the fuselage aftwardly of the wing structure. The engines are disposed side by side in a propulsive package disposed above the fuselage, which propulsive package includes the following, air inlet openings for the propulsive package, which openings are disposed above the fuselage between a point at the leading edge and a point at the trailing edge of an aerodynamic root chord of the wing structure; and exhaust nozzle conduit outlets associated with exhaust nozzle conduits, which outlets are formed by the structure (cowling structure) of the propulsive package, and are disposed above the fuselage forwardly of an aft terminus of the fuselage and between the vertical stabilizers. | ||||||
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