| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 41 | AFT ENGINE FOR AN AIRCRAFT | EP16188786.4 | 2016-09-14 | EP3144226B1 | 2018-11-21 | BECKER, Thomas Lee; MURROW, Kurt David; MARRINAN, Patrick Michael; MILLER, Brandon Wayne |
| A propulsion system for an aircraft (10) is provided having an aft engine configured to be mounted to the aircraft (10) at an aft end of the aircraft (10). The aft engine includes a fan (304) rotatable about a central axis of the aft engine having a plurality of fan blades (310). The aft engine also includes a nacelle (306) encircling the plurality of fan blades (310) with one or more structural members (308) extending between the nacelle (306) and the mean line (15) of the aircraft (10) at a location forward of the plurality of fan blades (310) when the aft engine is mounted to the aircraft (10). The aft engine may increase a net thrust of the aircraft (10) when mounted to the aircraft (10). | ||||||
| 42 | Methods and systems for minimizing flow disturbances in aircraft propeller blades caused by upstream pylons | EP10192028.8 | 2010-11-22 | EP2327628B1 | 2016-03-30 | Verde Preckler, Jorge Pablo; Caballero Asensio, María; Gustavsson, Mats |
| 43 | Flugzeugtriebwerk mit optimiertem Ölwärmetauscher | EP11001798.5 | 2011-03-03 | EP2366625A3 | 2013-12-25 | Todorovic, Predrag |
Die Erfindung bezieht sich auf ein Ejektor-Düsen-Rohr 1 mit einem über seine Länge im Wesentlichen gleichbleibenden, eine im Wesentlichen ovale Form aufweisenden hohlen Querschnitt, wobei an einem Strömungsvorderkantenbereich des Ejektor-Düsen-Rohrs 1 eine mit einem teilkreisförmigen Querschnitt versehene Anströmleiste 2 angeordnet ist, welche mit einer Vielzahl von Nuten 3 versehen ist, welche zur Oberfläche und zur Unterfläche des Ejektor-Düsen-Rohrs 1 münden 4 und mit einem durch das hohle Profil gebildeten Innenraum 5 des Ejektor-Düsen-Rohrs 1 in Verbindung sind, sowie auf ein Flugzeugtriebwerk mit optimiertem Ölwärmetauscher mit zumindest einem Ölkühler 6, welcher in einem Hinterkantenbereich 7 einer tragflügelartigen Struktur 8 angeordnet ist, wobei zumindest ein Strömungseinleitbereich 9 zur Zuführung einer Umgebungsluftströmung zu dem Ölkühler 6 vorgesehen ist, wobei der Ölkühler 6 in einem Strömungskanal 10 angeordnet ist und wobei stromab des Ölkühlers 6 in dem Strömungskanal 10 ein Ejektor-Düsen-Rohr 1 nach einem der Ansprüche 1 bis 3 angeordnet ist.
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| 44 | SUPERSONIC AIRCRAFT JET ENGINE | EP07873759 | 2007-10-10 | EP2084061A4 | 2013-07-24 | CHASE JAMES D; GARZON GERMAN ANDRES |
| 45 | AVION À EMPENNAGE QUEUE-DE-MORUE ET MOTEUR ARRIÈRE | EP10716387.5 | 2010-03-12 | EP2406133B1 | 2013-01-16 | CAZALS, Olivier; GENTY DE LA SAGNE, Jaime |
| 46 | AVION A MOTEURS PARTIELLEMENT ENCASTRES DANS LE FUSELAGE | EP09755936.3 | 2009-10-28 | EP2340203B1 | 2012-12-05 | CHANEZ, Philippe, Gérard; LECORDIX, Jean-Loïc, Hervé; THOMAS, Stéphane, Jacques, François |
| 47 | ENTREE D'AIR D'UN MOTEUR D'AVION A HELICES PROPULSIVES NON CARENEES | EP09760929.1 | 2009-11-09 | EP2344381B1 | 2012-08-01 | BENSILUM, Stéphane, Emmanuel, Daniel |
| 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 (A) of the engine between a point on the leading edge (138) of the air intake and a transverse plane (P) situated at an inlet impeller of the engine compressor, is longer (Lmax) in the region (142) of the air intake connected to the pylon and shorter (Lmin) in the region of the air intake opposite the pylon. | ||||||
| 48 | ENTRÉE D'AIR D'UN MOTEUR D'AVION À HÉLICES PROPULSIVES NON CARÉNÉES | EP09760929.1 | 2009-11-09 | EP2344381A1 | 2011-07-20 | BENSILUM, Stéphane, Emmanuel, Daniel |
| 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 (A) of the engine between a point on the leading edge (138) of the air intake and a transverse plane (P) situated at an inlet impeller of the engine compressor, is longer (Lmax) in the region (142) of the air intake connected to the pylon and shorter (Lmin) in the region of the air intake opposite the pylon. | ||||||
| 49 | AVION A MOTEURS PARTIELLEMENT ENCASTRES DANS LE FUSELAGE | EP09755936.3 | 2009-10-28 | EP2340203A1 | 2011-07-06 | CHANEZ, Philippe, Gérard; LECORDIX, Jean-Loïc, Hervé; THOMAS, Stéphane, Jacques, François |
| The invention relates to an airplane provided with dual-flow turbojet engines (12) having nacelles (16) at least partially encased in the fuselage (14), characterised in that the air intake of each engine (12) is connected to the fuselage by two boundary layer guiding walls (20), said walls (20) extending towards the upstream side of the air intake (18) and being spaced apart towards the upstream side. | ||||||
| 50 | Aircraft engine system with gearbox unit | EP08163626.8 | 2008-09-03 | EP2033893A2 | 2009-03-11 | Blumer, Eric W. |
An engine system (228) for an aircraft includes an engine (212,214) and a gearbox (220,222). The engine (112,114) is mounted in a nacelle region (216,218) of the aircraft. The gearbox (220,222) is coupled to the engine (212,214), and is mounted in a fuselage region of the aircraft. The nacelle region (216,218) is separated from the fuselage region (204) by a structure (230).
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| 51 | Multi-purpose aircraft | EP97109971.8 | 1994-08-24 | EP0798207A3 | 1998-04-08 | Gevers, David E. |
Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) (24,25) with a belt drive system (84,99) for turning wing-situated propellers (8,9); compound landing gear integrating ski (29,114), pontoon and wheel (18,19,21) subcomponents; pivotal mounting armatures (6,7) for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure (14,15) featuring extendable wing panels (4,5) that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water. |
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| 52 | MULTI-PURPOSE AIRCRAFT | EP95900354.0 | 1994-08-24 | EP0714363A1 | 1996-06-05 | Gevers, David E. |
| Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) (24,25) with a belt drive system (84,99) for turning wing-situated propellers (8,9); compound landing gear integrating ski (29,114), pontoon and wheel (18,19,21) subcomponents; pivotal mounting armatures (6,7) for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure (14,15) featuring extendable wing panels (4,5) that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water. |
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| 53 | Mounting assembly for unducted prop engine | EP89200171.0 | 1989-01-26 | EP0329211B1 | 1992-09-16 | Jacobs, Loyd D.; Shivashankara, Belur N. |
| 54 | AIRCRAFT WITH A VARIABLE FUSELAGE SURFACE FOR BOUNDARY LAYER OPTIMIZATION | US15849250 | 2017-12-20 | US20180201362A1 | 2018-07-19 | Alberto Arana Hidalgo; Raúl Carlos Llamas Sandín; Jesús Javier Vázquez Castro |
| An aircraft including a propulsion system formed by engines arranged to ingest boundary layer air. These engines are placed inside of nacelles partially embedded in the aircraft fuselage and, thus, their intake conduits are delimited by specific fuselage areas and the nacelles. For the specific fuselage areas skins are disclosed with a flexible portion and actuation systems over them for changing their surfaces to adapt them to the needs of the propulsion system. | ||||||
| 55 | TRANSLATING NACELLE WALL FOR AN AIRCRAFT TAIL MOUNTED FAN SECTION | US15282098 | 2016-09-30 | US20180093777A1 | 2018-04-05 | Lawrence Chih-hui Cheung |
| The present disclosure is directed to a fan section positioned on a tail section of an aircraft, in which the fan section defines a circumferential direction, a radial direction, and an axial direction. The fan section includes a fan and a nacelle. The fan includes a plurality of fan blades and a fan shaft, in which the plurality of fan blades are rotatable with the shaft. The nacelle includes a wall at least partially enclosing the fan. The wall includes a first portion and a second portion. The first portion translates relative to the second portion between a first, closed position in which the wall of the nacelle circumferentially encloses the fan and a second, open position in which at least a portion of the fan is unenclosed by the wall of the nacelle. | ||||||
| 56 | AIRCRAFT HAVING AN AFT ENGINE | US15275596 | 2016-09-26 | US20180086438A1 | 2018-03-29 | Nikolai N. Pastouchenko; Ivan Malcevic |
| An aircraft is provided including a boundary layer ingestion fan mounted to an aft end of a fuselage. A stabilizer is mounted to the fuselage and extends between a root portion and a tip portion to define a span-wise length and extends between a leading edge and a trailing edge along the longitudinal direction. The stabilizer defines a line of maximum thickness that corresponds to the thickest cross sectional portion of the stabilizer along the span-wise length of the stabilizer. The line of maximum thickness is closer to the leading edge of the stabilizer proximate the root portion than at the tip portion, resulting in a pressure distribution that draws higher velocity air away from an inlet of the boundary layer ingestion fan. | ||||||
| 57 | AFT ENGINE NACELLE SHAPE FOR AN AIRCRAFT | US15794648 | 2017-10-26 | US20180057182A1 | 2018-03-01 | Patrick Michael Marrinan; Thomas Lee Becker; Kurt David Murrow; Jixian Yao |
| An aircraft is provided including a fuselage and an aft engine. The fuselage defines a top side, a bottom side, and a frustum located proximate an aft end of the aircraft. The frustum defines a top reference line extending along the frustum at a top side of the fuselage, and a bottom reference line extending along the frustum at a bottom side of the fuselage. The top and bottom reference lines meet at a reference point aft of the frustum. The fuselage further defines a recessed portion located aft of the frustum and indented inwardly from the bottom reference line. The aft engine includes a nacelle extending adjacent to the recessed portion of the fuselage such that the aft engine may be included with the aircraft without interfering with, e.g., a takeoff angle of the aircraft. | ||||||
| 58 | DEPLOYABLE ASSEMBLY FOR A PROPULSOR | US15244032 | 2016-08-23 | US20180057150A1 | 2018-03-01 | Lawrence Chih-hui Cheung; Nikolai N. Pastouchenko; Kishore Ramakrishnan |
| An aircraft includes a fuselage extending between a forward end and an aft end. The aircraft additionally includes a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor including an outer nacelle and the outer nacelle defining an inlet. Additionally, the aircraft includes a deployable assembly attached to at least one of the fuselage or the outer nacelle, the deployable assembly movable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position to increase an efficiency of the aft fan and/or of the aircraft. | ||||||
| 59 | AIRCRAFT COMPRISING A TURBOJET ENGINE INTEGRATED INTO THE REAR FUSELAGE COMPRISING A FAIRING ALLOWING THE EJECTION OF BLADES | US15659546 | 2017-07-25 | US20180030852A1 | 2018-02-01 | Nicolas Jerome Jean TANTOT; Michael SAUVE |
| The invention relates to an aircraft comprising a fuselage, flight control surfaces and a turbojet engine (20) integrated into the rear of said fuselage in the extension thereof, the turbojet engine (12) comprising two gas generators (22) that supply, via a common central duct (30), a power turbine (32) comprising two counter-rotating rotors (34, 36) respectively driving two upstream (38) and downstream (40) coaxial and counter-rotating fans each comprising a ring of vanes (42, 44), the set of fans (38, 40) being integrated into a fairing (46) of the turbojet engine (20) formed at the rear of the fuselage (12), characterised in that at least said fairing (46) is axially arranged behind the flight control surfaces and comprises an upstream section (50), surrounding the upstream fan (38), configured to be radially traversed by at least one fragment (43) of a vane (42) of the upstream fan (38) in the event of the breakage of a vane (42) of said upstream fan (38) and the ejection of said at least one fragment (43). | ||||||
| 60 | Aircraft engine mounting system | US15359965 | 2016-11-23 | US09868540B2 | 2018-01-16 | Sergey D. Barmichev; David W. Kirkbride; Mithra M. K. V. Sankrithi |
| An aircraft includes an engine mounted to a wing by a first support, such as a strut, configured to secure the engine to the wing in a position above the wing. A second support, secured to a fuselage portion of the aircraft, is defined by a bridge structure configured to separately and independently secure the engine to the fuselage. The engine is thus secured by the first support directly to the aircraft wing, and via the second support, in concert with the first, to a portion of an aircraft fuselage spaced laterally of the engine-to-wing attachment. In one embodiment the bridge structure, which extends between the engine and fuselage, may be bowed upwardly so as to define a convex curvature when viewed along the longitudinal axis of the aircraft. Such a curvature may, inter alia, optimize aerodynamic spacing of the bridge from the wing to minimize undesirable shock waves. | ||||||
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