| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 141 | PYLON WITH NOISE ATTENUATING FAIRING | US14746439 | 2015-06-22 | US20160368616A1 | 2016-12-22 | Michael Aten |
| A pylon is provided for connecting a propulsion system to an aircraft. The pylon includes a structure configured to structurally tie the propulsion system to the aircraft. The pylon also includes a pylon fairing configured to house and provide an aerodynamic cover for the structure. A lower aft fairing segment of the pylon fairing includes a plurality of apertures. The apertures are fluidly coupled with a sealed, sound attenuating chamber within the pylon. | ||||||
| 142 | EXTREMELY QUIET SHORT TAKE-OFF AND LANDING (STOL) AIRCRAFT | US14687277 | 2015-04-15 | US20160318606A1 | 2016-11-03 | Kyle RAHRIG; Geoffrey SOMMER; Barnaby S. WAINFAN |
| An extremely quiet short take-off and landing (STOL) aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage in an orientation that is rotated relative to the typical orientation on a helicopter. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system; a fuselage structurally connected to each wing; channel shrouds surrounding at least one of the engine systems; and a ducted fan thruster positioned on the fuselage. An extremely quiet STOL aircraft includes: two wings, wherein each wing comprises an engine system, the engine system comprising two engine dual packs; a fuselage structurally connected to each wing; and a ducted fan thruster positioned on the fuselage. | ||||||
| 143 | Aerodynamic fairing divided into sub-portions | US14501910 | 2014-09-30 | US09469409B2 | 2016-10-18 | Francois Peyruseigt; Thierry Gaches; Mathieu Kaleta; Nicolas Voyer; Delphine Chamaillard |
| An aerodynamic fairing including at least one sub-assembly, each sub-assembly having a frame which is orientated transversely relative to the longitudinal axis of the fairing and a floor portion which is provided with an inner face, via which the floor portion is fixed to the frame. The fairing further comprises lateral panels which are fixed to the frame and which each extend substantially along the longitudinal axis of the fairing at one side and the other of a plane of symmetry of the fairing. The floor portions of the sub-assemblies are not mechanically connected to each other via rigid connections. The division of the floor into separate portions allows a reduction in the longitudinal thermomechanical stresses applied by the expansion of the floor under the action of the primary hot flow of the turbo reactor. | ||||||
| 144 | System and method for cooling an aircraft wing | US14360925 | 2011-11-29 | US09452841B2 | 2016-09-27 | John Richardson |
| An aircraft comprises a turbine engine suspended from a wing by means of a pylon. Compressed hot air is bled off from the turbine engine. A bleed air duct in the wing conveys the compressed hot air towards a fuselage. In order to prevent overheating of aircraft parts that are relatively close to the bleed air duct, the following solution is proposed. The pylon comprises an opening with a covering structure projecting into a bypass exhaust flow from the turbine engine. The covering structure leaves a slit facing away from the bypass exhaust flow. An airflow path extends from openings in the wing to the slit left by the covering structure. | ||||||
| 145 | NOSE CONE STRUCTURE FOR PYLON OF AIRCRAFT WITH WING-HUNG LAYOUT | US14892919 | 2014-08-28 | US20160272335A1 | 2016-09-22 | YINGCHUN CHEN; MIAO ZHANG; ZHEHUI YU; MEIHONG ZHANG; FEI XUE; TIEJUN LIU; DONGYUN ZHANG; FENG ZHOU; TULIANG MA; BINBIN ZHAO |
| An aircraft with a wing-hung layout has a nose cone structure for a pylon. A front nose cone is located in front of a wing leading edge, and a rear nose cone is located behind the wing leading edge. At least a part of the rear nose cone is modeled and shaped by cross section control lines and has at least one group of horizontal position control lines and at least one group of longitudinal position control lines. The rear nose cone of the pylon is shaped by horizontal position control lines. By controlling the rear nose cone curvature of the pylon the passageway area of the space between the pylon/wing/engine nacelle is optimized without deflection of the rear portion of the pylon. | ||||||
| 146 | CONVERGENT DIVERGENT EXIT NOZZLE FOR A GAS TURBINE ENGINE | US14817611 | 2015-08-04 | US20160195038A1 | 2016-07-07 | Dmitriy B. Sidelkovskiy; Oleg Petrenko; Robert E. Malecki; Steven H. Zysman |
| A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle. | ||||||
| 147 | FOLDABLE GUIDING VENTILATOR COVER FOR AN AIRCRAFT ENGINE ASSEMBLY | US14811152 | 2015-07-28 | US20160031563A1 | 2016-02-04 | Olivier Pautis |
| For gains in terms of aerodynamic performance levels, an aircraft engine assembly includes a turbomachine, a fastening strut for the turbomachine, and at least one foldable ventilator cover which surrounds the turbomachine and which includes: a first cover sector which includes a first end portion which is mounted so as to be articulated to the fastening strut, along a first articulation axis, and a second cover sector which includes a first end portion which is mounted so as to be articulated to a second end portion of the first cover sector, along a second articulation axis parallel with the first articulation axis. The second end portion is mounted so as to be guided at one side and the other thereof by a thrust inverter cover of the engine assembly and an air inlet structure of this assembly, respectively. | ||||||
| 148 | AIRCRAFT PROPULSION ASSEMBLY COMPRISING AT LEAST ONE BRUSH SEAL RESISTANT TO HIGH-TEMPERATURE | US14762085 | 2014-01-20 | US20150367947A1 | 2015-12-24 | Virginie Audart-Noel; Benoit Letay; Loïc Dussol; Michael Galinier; Nicolas Viallet; Laurent Cazeaux; Benjamin Vignoboul |
| A seal is interposed between two surfaces of an aircraft propulsion assembly. The seal includes at least two layers each comprising a plurality of strands made of a heat-resistant material, the strands of a first layer being oriented in a first orientation and the strands of a second layer being oriented in a second orientation different than the first orientation. | ||||||
| 149 | Nacelle-To-Pylon Fairing | US14270485 | 2014-05-06 | US20150321766A1 | 2015-11-12 | Sean P. Howe; Christopher L. Gromek; Anish A. Taylor |
| A nacelle-to-pylon fairing formed over at least a portion of an inter-region between a nacelle and a pylon of an aircraft may include a longitudinal axis, a lateral axis and a transverse axis, an upper end incorporated to the pylon at a fairing-to-pylon interface, and a lower end incorporated to the nacelle at a fairing-to-nacelle interface, wherein the fairing defines a surface between the upper end and the lower end. | ||||||
| 150 | NON-CIRCULAR AFT NACELLE COWLING GEOMETRY | US14676354 | 2015-04-01 | US20150247425A1 | 2015-09-03 | Michael J. Murphy; Robert E. Malecki |
| A nacelle for a turbofan propulsion system that extends along a centerline includes a forward cowling and an aft cowling. To improve the fit of a turbofan propulsion system in the space between the wing and ground of a fixed-wing aircraft, the aft cowling of the nacelle is modified. The aft cowling has a non-circular cross-sectional geometry disposed in a plane substantially perpendicular to the centerline. The non-circular cross-sectional geometry includes a radially recessed section disposed between first and second curved sections. The first and the second curved sections each have a radius that is greater than a radial distance between the centerline and a center point of the radially recessed section. | ||||||
| 151 | ROTATIONAL DUCTED FAN (RDF) PROPULSION SYSTEM | US14095737 | 2014-02-03 | US20150226086A1 | 2015-08-13 | Devin Glenn Samuelson |
| In accordance with the present invention, an embodiment of a rotational ducted fan motor comprises a monolithic rotational ducted fan rotor, an electric propulsion system, a static aft-shroud comprising electrochemical-energy-storage, and an engagement system. The rotational ducted fan rotor is the portion of a ducted fan motor comprising a propeller, a duct, and a center hub, and having the effect of increasing the pressure difference from upstream to downstream of the propeller. The electric propulsion system comprises permanent magnets affixed to the rotational ducted fan rotor, repelling magnetic coils affixed to the static aft-shroud and electrical power provided by the electrochemical-energy-storage comprised within the aft-shroud. | ||||||
| 152 | Engine pylon comprising a vortex generator, and method for the production thereof | US13508283 | 2010-10-27 | US08936213B2 | 2015-01-20 | Steve Bedoin; Cyril Bonnaud |
| The invention relates to a method for manufacturing an engine pylon (7) to be mounted between an engine (1) and an aircraft wing (6), said method comprising: mounting a pylon box (8) around a main structure (9), the box having a substantially oblong shape along which an air boundary layer (C) is formed while in flight; mounting at least one vortex generator (2) onto the pylon box such that a thickness (e) of the boundary layer is changed; and previously determining the shape of the pylon on the basis of the changed thickness of the boundary layer and the position of the vortex generators. | ||||||
| 153 | Nacelle | US14246352 | 2014-04-07 | US08931736B2 | 2015-01-13 | Michael Ray Aten; Sara Crawford |
| A nacelle is configured to be coupled to an underside of a wing and forms a clearance space between the nacelle and a leading edge slat of the wing. A portion of an outlet cowling moves longitudinally aft when a reverse thrust configuration is activated and the leading edge slat is deployed toward the nacelle. The outlet cowling also includes another portion located adjacent to the leading edge slat that does not move when the reverse thrust configuration is activated and thus maintains its clearance space from the leading edge slat. | ||||||
| 154 | ATTACHMENT PYLON FOR A TURBINE ENGINE | US14356045 | 2012-10-24 | US20140290270A1 | 2014-10-02 | Guillaume Bodard; Cyprien Henry; Norman Jodet; Alexandre Alfred, Gaston Vuillemin |
| A pylon for attaching a turbine engine, the pylon configured to connect the engine to a structural element of an aircraft. The pylon includes a streamlined profile defined by two opposite lateral faces and defined longitudinally between a leading edge and a trailing edge. On each of its lateral faces the pylon includes a series of deflectors that are transversely spaced apart from one another and that define between them convergent and curved channels configured to accelerate air streams flowing within the channels on aircraft takeoff or in flight to deflect the air streams towards a jet of the engine. | ||||||
| 155 | Aft pylon fairing for aircraft engine suspension system, comprising a heat shield capable of expanding freely | US13653042 | 2012-10-16 | US08844862B2 | 2014-09-30 | Frédéric Journade |
| This invention relates to an aft pylon fairing for the suspension system of an aircraft engine, comprising a main structure extending along a longitudinal direction of said fairing and integrating two side panels connected to each other, the fairing also comprising a heat protection deck mounted on said main structure through connection means comprising tabs designed to deform to accompany displacement of the deck relative to the main structure, if there is differential thermal expansion between these two entities. | ||||||
| 156 | Engine nacelle of an aircraft comprising a vortex generator arrangement | US12663094 | 2008-06-16 | US08827210B2 | 2014-09-09 | Detlev Schwetzler |
| An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor situated between two boundary lines, wherein: the starting point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=35 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the first boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=25 degrees and the engine-nacelle longitudinal coordinate X=L·⅔; the starting point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=90 degrees and the engine-nacelle longitudinal coordinate X=L/4; the end point of the second boundary line is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi=55 degrees and the engine-nacelle longitudinal coordinate X=L·⅔. | ||||||
| 157 | Aerodynamic aft fairing of an aircraft engine suspension pylon | US13534967 | 2012-06-27 | US08814080B2 | 2014-08-26 | Jean-François Dumont; Marc Lefort |
| An aerodynamic aft fairing of an engine pylon ensuring the mounting of an engine underneath a wing of an aircraft is provided. The aerodynamic aft fairing includes an outer lateral panel and an inner lateral panel assembled together at least by a bottom panel, the bottom panel comprising, on either side of the lateral panels, an extension forming an aerothermic barrier capable of channeling hot air flows leaving the engine. The inner lateral panel and the outer lateral panel are attached to the bottom panel by a first angle bar and a second angle bar, respectively. | ||||||
| 158 | Aircraft engine pylon AFT aerodynamic fairing | US13682138 | 2012-11-20 | US08800917B2 | 2014-08-12 | Stephane Machado; Fabien Raison; Stephane Romani |
| An aircraft engine pylon aft aerodynamic fairing includes upper spars, transverse stiffening ribs, lower spars and a trailing edge where the upper spars and lower spars join together. In this fairing, a profiled structure is formed according to a profile open to the outside of the fairing. In a first end portion, the profiled structure comes to be enclosed between an end portion of the lower spars and the ends of at least one transverse stiffening ribs flush with the lower spars. This structure extends between the lower spars and the upper spars over a straight central portion inclined relative to the first end portion, and comes in a second end portion flush against a portion of the upper spars, parallel to the first end. | ||||||
| 159 | Jet engine installation | US13170702 | 2011-06-28 | US08651426B2 | 2014-02-18 | Romuald Morvant; Kevin M Britchford |
| Noise generated by a gas turbine engine 6 supported by a pylon 8 on a wing 2 of an aircraft is reduced by influencing a shear layer generated between the free-stream flowfield and flow from the engine 6. The shear layer is influenced by means of one or more winglets 18, 20, 22 which interact with the free-stream flowfield to deflect the shear layer 14 downwardly, to avoid interaction with a flap 4 on the wing 2, or to reduce the strength of the shear layer 14. | ||||||
| 160 | Method of manufacture by superplastic forming and by fishplating of a rib for an aerodynamic fairing of an aircraft engine mounting pylon | US13115408 | 2011-05-25 | US08607453B2 | 2013-12-17 | Stephane Machado; Fabien Raison; Stephane Romani |
| The present invention relates to a method of manufacture of a group of transverse internal stiffening ribs (46) for an aerodynamic fairing of an engine mounting device, including: production, for each rib (46), of a given rib preform (46a) by superplastic forming; and in respect of at least one of the ribs (46) of the group having a smaller size than that of the preform (46a), division of the latter into four preform parts (56a-56d) each incorporating one of the four corners of the quadrilateral formed by the preform, followed by the joining of the four parts to one another so as to obtain the rib. | ||||||
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