| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Non-handed engine cowl doors for fuselage mounted turbine engines | US12020843 | 2008-01-28 | US08016227B2 | 2011-09-13 | Mike Hammer |
| An engine cowl door assembly is provided for fuselage mounted turbine engines to minimize manufacturing costs and part counts. In one embodiment, the engine cowl door assembly includes at least one non-handed engine cowl door, a pylon apron coupled to the fuselage of an aircraft and providing an attachment point for a first portion of the engine cowl door and a fairing coupled to the turbine engine and providing a latching point for a second portion of the engine cowl door to the turbine engine. The pylon apron, positioned on an inboard side of the turbine engine, and the fairing, positioned on an outboard side of the turbine engine, are identically shaped to provide interchangeability of the engine cowl door from a turbine engine mounted on a first side of an aircraft fuselage to a turbine engine mounted on a opposed second side of an aircraft fuselage. | ||||||
| 82 | COOLING DEVICE FOR AIRCRAFT PROPELLER | US13013319 | 2011-01-25 | US20110179767A1 | 2011-07-28 | Christelle RINJONNEAU; Pierre GUILLAUME |
| The invention relates to an aircraft propeller (1) comprising a turbomachine (8) housed in a nacelle (10) and a cooler (45) capable of being traversed by a hot fluid, which is to be cooled by thermal exchange with cold air external to the cooler. The propeller (1) comprises an air stream (13) (13b) capable of directing pressurized air towards an air duct (20) realized between an outer wall (6) and an inner wall (60) of the nacelle (10). The cooler comprises volumetric cooling means (14) located in the air duct (20) and surface cooling means (15), unrelated to said volumetric cooling means, located at an outside wall (6, 101) of the aircraft. | ||||||
| 83 | Supersonic aircraft jet engine installation | US12807142 | 2010-08-30 | US07967241B2 | 2011-06-28 | 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 xl) 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. | ||||||
| 84 | Inverted airfoil pylon for an aircraft | US11644712 | 2006-12-22 | US07770841B2 | 2010-08-10 | 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. | ||||||
| 85 | NON-HANDED ENGINE COWL DOORS FOR FUSELAGE MOUNTED TURBINE ENGINES | US12020843 | 2008-01-28 | US20090189013A1 | 2009-07-30 | Mike Hammer |
| An engine cowl door assembly is provided for fuselage mounted turbine engines to minimize manufacturing costs and part counts. In one embodiment, the engine cowl door assembly includes at least one non-handed engine cowl door, a pylon apron coupled to the fuselage of an aircraft and providing an attachment point for a first portion of the engine cowl door and a fairing coupled to the turbine engine and providing a latching point for a second portion of the engine cowl door to the turbine engine. The pylon apron, positioned on an inboard side of the turbine engine, and the fairing, positioned on an outboard side of the turbine engine, are identically shaped to provide interchangeability of the engine cowl door from a turbine engine mounted on a first side of an aircraft fuselage to a turbine engine mounted on a opposed second side of an aircraft fuselage. | ||||||
| 86 | Aircraft propulsive power unit | US10261832 | 2002-09-30 | US06869046B2 | 2005-03-22 | Finbarr McEvoy |
| An aircraft having a propulsive power unit supported in a fuselage mounted configuration and including an engine and a nacelle structure housing the engine. The nacelle structure is provided with upper and lower displaceable nacelle portions, such as thrust reverser cowls and fan cowl doors which are displaceable between closed dispositions which they occupy during operational conditions of the aircraft and open dispositions which they take up to provide access to engine components. The upper and lower nacelle portions are so mounted as to be displaceable to their open and closed dispositions in movements in which one is assisted by gravitational force and the other is displaced against gravitational force. A force transfer mechanism is provided for transfer during opening and closing movements of the nacelle portions of gravitational force assisting displacement of one of the nacelle portions to assist in displacement of the other nacelle portion being displaced against gravitational force. | ||||||
| 87 | Twin engine aircraft | US09143047 | 1998-08-28 | US06170780B2 | 2001-01-09 | Sam Barlow Williams |
| A jet aircraft has an elongated fuselage with an intermediate section of maximum lateral cross section, a generally conical aft fuselage section of relatively smaller cross section and a single vertical stabilizer extending upwardly from the aft fuselage section. The aircraft's propulsion engines are mounted on the vertical stabilizer with the air inlets thereof spaced from the fuselage and vertical stabilizer yet disposed entirely within a rearward projection of the lateral cross section of the intermediate fuselage section thereby to preclude the ingestion of foreign objects into the engines while minimizing the effect of boundary layer airflow. | ||||||
| 88 | Multi-purpose aircraft | US195920 | 1998-11-19 | US6098927A | 2000-08-08 | David E. Gevers |
| Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels 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. | ||||||
| 89 | Pylon flap for increasing negative pitching moments | US751929 | 1996-11-12 | US5779191A | 1998-07-14 | Mark G. Brislawn |
| First and second pylon flaps are located on aft portions of the first and second jet engine pylons, respectively. The first and second pylon flaps are moveable between retracted pylon flap angular orientations and extended pylon flap angular orientations. The first and second pylon flaps can assume only fully retracted angular orientations and fully extended angular orientations. When the T-tailed aircraft enters into a deep stall condition, the pilot will more than likely push the control column forward to its maximum position. This full forward movement of the control column commands the first and second pylon flaps to assume fully extended angular orientations. A first pylon flap controller controls the first pylon flap to move between the fully extended and fully retracted angular orientations, and a second pylon flap controller controls the second pylon flap to move between the fully extended and fully retracted angular orientations. | ||||||
| 90 | AIRCRAFT | EP16166183.0 | 2016-04-20 | EP3093235B1 | 2018-11-21 | Moxon, Matthew |
| An aircraft (10) comprises trailing edge flaps (17), a wing mounted propulsor (26) positioned such that the flaps (17) are located in a slipstream of the first propulsor in use when deployed. The aircraft (10) further comprises a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor comprises a ducted fan (30) configurable between a first mode, in which the fan (30) provides net forward thrust to the aircraft (10), and a second mode in which the fan (30) provides net drag to the aircraft. (10). The fan (30) is positioned to ingest a boundary layer airflow in use when operating in the first mode. | ||||||
| 91 | DISPOSITIF DE REDUCTION DE TRAINEE AERODYNAMIQUE | EP08853244.5 | 2008-11-21 | EP2242691B1 | 2017-03-01 | RAYMOND, Gérald; BOURDIEU, Philippe |
| 92 | SUPERSONIC AIRCRAFT JET ENGINE | EP07873759.0 | 2007-10-10 | EP2084061B1 | 2016-12-14 | CHASE, James, D.; GARZON, German, Andres |
| 93 | A boundary layer energiser | EP10177123.6 | 2010-09-16 | EP2317108B1 | 2015-11-11 | Sheaf, Christopher; Hussain, Zahid |
| 94 | Flugzeugtriebwerk mit optimiertem Ölwärmetauscher | EP11001798.5 | 2011-03-03 | EP2366625B1 | 2015-05-20 | Todorovic, Predrag |
| 95 | PARTIE ARRIERE D'AERONEF COMPRENANT UNE STRUCTURE DE SUPPORT DE MOTEURS RELIEE AU FUSELAGE PAR AU MOINS UN ELEMENT DE BLOCAGE SOLLICITE EN COMPRESSION | EP09748398.6 | 2009-09-16 | EP2334554B1 | 2012-01-18 | LAFONT, Laurent; JOURNADE, Frédéric |
| The invention relates to a rear part of an aircraft (1) comprising a structure for supporting engines (14), passing through the fuselage, through a first opening and a second opening (18, 18). Said rear part comprises connection means connecting the support structure (14) to the fuselage (6), with first connection means connecting the structure (14) to a first casing (50) forming the first opening and second connection means connecting the structure (14) to a second casing (50) forming the second opening. According to the invention, the first and second connection means each comprise at least one blocking element (90, 92) of said support structure, under compression loading by being applied to the casing (50) and to the support structure (14). | ||||||
| 96 | Flugzeugtriebwerk mit optimiertem Ölwärmetauscher | EP11001798.5 | 2011-03-03 | EP2366625A2 | 2011-09-21 | 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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| 97 | PARTIE ARRIERE D'AERONEF COMPRENANT UNE STRUCTURE DE SUPPORT DE MOTEURS TRAVERSANT LE FUSELAGE ET RELIEE A CELUI-CI PAR AU MOINS UNE BIELLE | EP09747884.6 | 2009-09-16 | EP2334556A1 | 2011-06-22 | LAFONT, Laurent; JOURNADE, Frédéric; JALBERT, Delphine; BARDOU, Etienne |
| The invention relates to a rear part of an aircraft (1) comprising a structure for supporting engines (14), extending through the fuselage, through a first opening and a second opening (18, 18). Said rear part comprises connection means connecting the structure (14) to the fuselage (6), with first connection means connecting the structure to a first casing (50) forming the first opening (18) and second connection means connecting the structure to a second casing (50) forming the second opening (18). According to the invention, the connection means also comprise at least one effort recovery connecting rod (66), the first end of which is mounted on the structure (14) and the opposite end is mounted on the fuselage, at a distance from the first and second openings. | ||||||
| 98 | PARTIE ARRIERE D'AERONEF COMPRENANT UNE STRUCTURE DE SUPPORT DE MOTEURS RELIEE AU FUSELAGE PAR AU MOINS UN ELEMENT DE BLOCAGE SOLLICITE EN COMPRESSION | EP09748398.6 | 2009-09-16 | EP2334554A1 | 2011-06-22 | LAFONT, Laurent; JOURNADE, Frédéric |
| The invention relates to a rear part of an aircraft (1) comprising a structure for supporting engines (14), passing through the fuselage, through a first opening and a second opening (18, 18). Said rear part comprises connection means connecting the support structure (14) to the fuselage (6), with first connection means connecting the structure (14) to a first casing (50) forming the first opening and second connection means connecting the structure (14) to a second casing (50) forming the second opening. According to the invention, the first and second connection means each comprise at least one blocking element (90, 92) of said support structure, under compression loading by being applied to the casing (50) and to the support structure (14). | ||||||
| 99 | Methods and systems for minimizing flow disturbances in aircraft propeller blades caused by upstream pylons | EP10192028.8 | 2010-11-22 | EP2327628A2 | 2011-06-01 | Verde Preckler, Jorge Pablo; Caballero Asensio, María; Gustavsson, Mats |
Methods for minimizing the effects of pylon induced disturbances of the airflow at the propeller blades (2) of propeller propulsion devices (3) attached to an aircraft component (5) by means of upstream pylons (4), comprising steps of injecting fluid on the zone of the propeller blades (2) from the rear part of said pylons (4) for minimizing the effects of said disturbances detected through the values of a first set of parameters such acoustic pressure and vibration in the aircraft structure and vibration in the propeller blades (2) that are obtained continuously or according to models linked to one or more parameters of a second set of parameters indicative of the aircraft flight conditions such as flight altitude, flight speed propulsion power, propeller rotation speed obtained from a tachometer signal, ambient temperature of the air. The invention also refers to systems for implementing said methods.
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| 100 | A boundary layer energiser | EP10177123.6 | 2010-09-16 | EP2317108A2 | 2011-05-04 | Sheaf, Christopher; Hussain, Zahid |
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.
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