| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | AFT ENGINE FOR AN AIRCRAFT | US14859514 | 2015-09-21 | US20170081035A1 | 2017-03-23 | Thomas Lee Becker; Kurt David Murrow; Patrick Michael Marrinan; Brandon Wayne Miller |
| A propulsion system for an aircraft is provided having an aft engine configured to be mounted to the aircraft at an aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine having a plurality of fan blades. The aft engine also includes a nacelle encircling the plurality of fan blades with one or more structural members extending between the nacelle and the mean line of the aircraft at a location forward of the plurality of fan blades when the aft engine is mounted to the aircraft. The aft engine may increase a net thrust of the aircraft when mounted to the aircraft. | ||||||
| 162 | AIRCRAFT HAVING AN AFT ENGINE | US14859549 | 2015-09-21 | US20170081013A1 | 2017-03-23 | 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. | ||||||
| 163 | AIRCRAFT | US15135040 | 2016-04-21 | US20160332741A1 | 2016-11-17 | Matthew MOXON |
| An aircraft including trailing edge flaps, a wing mounted propulsor positioned such that the flaps are located in a slipstream of the first propulsor in use when deployed. The aircraft further including a thrust vectorable propulsor configured to selectively vary the exhaust efflux vector of the propulsor in at least one plane. The thrust vectorable propulsor includes a ducted fan configurable between a first mode, in which the fan provides net forward thrust to the aircraft, and a second mode in which the fan provides net drag to the aircraft. The fan is positioned to ingest a boundary layer airflow in use when operating in the first mode. | ||||||
| 164 | REVERSE CORE ENGINE WITH THRUST REVERSER | US14774896 | 2014-03-12 | US20160017844A1 | 2016-01-21 | Gabriel L Suciu; Jesse M Chandler |
| An engine system has a gas generator, a bi-fi wall surrounding at least a portion of the gas generator, a casing surrounding a fan, and the casing having first and second thrust reverser doors which in a deployed position abut each other and the bi-fi wall. | ||||||
| 165 | ATTACHMENT PYLON FOR AN UNDUCTED FAN | US14364981 | 2012-12-12 | US20140374566A1 | 2014-12-25 | Rasika Fernando; Nicolas Mehier; Fabien Monti; Nicolas Sirvin |
| A pylon configured to secure a turbine engine to a structural element of an aircraft, the pylon including a streamlined profile defined by two opposite faces and extending longitudinally between a leading edge and a trailing edge, and at least a first one of the two faces presenting at least locally a succession of non-through hollows and of bumps. | ||||||
| 166 | Aircraft with electric propulsion means | US14304864 | 2014-06-13 | US20140367510A1 | 2014-12-18 | Stéphane Viala; Jason Zaneboni; Bruno Saint-Jalmes |
| An aircraft with an electric propulsion arrangement which includes a fuselage, a wing system attached to the fuselage, and a tail unit attached to a rear part of the fuselage. The electric propulsion arrangement is arranged on each side of the fuselage, an electrical energy generator and electricity storage and supply devices are arranged substantially along a longitudinal axis of symmetry of the fuselage. The aircraft thus incorporates a hybrid motorization. | ||||||
| 167 | Ejector driven flow control for reducing velocity deficit profile downstream of an aerodynamic body | US12723678 | 2010-03-14 | US08690106B1 | 2014-04-08 | Mark A. Reissig |
| A system and method for reducing a velocity deficit from an aerodynamic body is disclosed. An air jet is injected into an ejector mixing chamber in the aerodynamic body. The air jet creates a suction effect in the ejector mixing chamber, which suctions boundary layer air from a perforated surface in at least one side of the aerodynamic body into a plenum chamber and into the ejector mixing chamber. The air jet ejects the boundary layer air and the air jet from a trailing edge slot of the ejector mixing chamber. Suctioning the boundary layer air and ejecting the boundary layer air and the air jet from the trailing edge slot reduces a velocity deficit on a trailing edge of the aerodynamic body. The reduced velocity deficit and the suctioning of boundary layer air reduce noise, turbulence, blade stress, and blade deformation. | ||||||
| 168 | Air ejector nozzle tube for an oil heat exchanger of an aircraft engine | US13039795 | 2011-03-03 | US08690098B2 | 2014-04-08 | Predrag Todorovic |
| An ejector nozzle tube, having along its length an essentially constant, essentially oval hollow cross-section, with a leading edge nozzle, having a rounded exterior cross-section, being arranged at a flow leading-edge area of the ejector nozzle tube. The leading edge nozzle includes a plurality of grooves issuing to the top and bottom sides of the ejector nozzle tube and connecting to an interior of the ejector nozzle tube formed by the hollow profile. An aircraft engine has an optimized oil heat exchanger with at least one oil cooler disposed in a trailing-edge area of an aerofoil-type structure, with at least one flow entrance area being provided to supply ambient air to the oil cooler disposed in a flow duct. The ejector nozzle tube can be arranged downstream of the oil cooler in the flow duct. | ||||||
| 169 | Airplane having engines partially encased in the fuselage | US13061634 | 2009-10-28 | US08684302B2 | 2014-04-01 | 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. | ||||||
| 170 | Airplane with a tailcoat tail assembly and rear engine | US13255720 | 2010-03-12 | US08651414B2 | 2014-02-18 | Olivier Cazals; Jaime Genty De La Sagne |
| An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage. | ||||||
| 171 | Aircraft with reciprocating engines partially embedded in the fuselage | US12582262 | 2009-10-20 | US08573532B2 | 2013-11-05 | Jean-Loic Herve Lecordix; Marc Patrick Tesniere; Stephane Jacques Francois Thomas |
| An aircraft provided with turbojet engines of which the nacelles are partially embedded in the fuselage of the aircraft is disclosed. The aircraft includes an internal space at engine nacelles. The internal space includes a platform capable of supporting personnel and maintenance equipment, with the portions of the nacelles located inside the aircraft comprising trapdoors or devices for accessing inside the engines from the platform. | ||||||
| 172 | Rear part of an aircraft comprising a structure for supporting engines, connected to the fuselage by at least one blocking element under compression loading | US13063080 | 2009-09-16 | US08448897B2 | 2013-05-28 | Laurent Lafont; Frederic Journade |
| A rear part of an aircraft including a support structure for supporting engines, passing through the fuselage, through first and second openings. The rear part includes a connection structure connecting 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 first and second connection mechanisms each include at least one blocking element of the support structure, under compression loading by being applied to the casing and to the support structure. | ||||||
| 173 | STREAMLINED PROFILE REDUCING THE SPEED DEFICIT IN ITS WAKE | US13454469 | 2012-04-24 | US20120273609A1 | 2012-11-01 | Damien Prat; Camil Negulescu; Frederic Barrois; Bastien Caruelle |
| The invention relates to a streamlined profile reducing the speed deficit in its wake, a pylon comprising such a profile, a propulsion assembly including such a pylon and an aircraft including this assembly. The profile comprises a device (40) for suction of air from the boundary layer formed on this profile. This suctioned air is discharged with the aid of a nozzle (48) 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. | ||||||
| 174 | AIRPLANE WITH A TAILCOAT TAIL ASSEMBLY AND REAR ENGINE | US13255720 | 2010-03-12 | US20120138736A1 | 2012-06-07 | Olivier Cazals; Jaime Genty De La Sagne |
| An airplane, including a fuselage having an elongate shape along a longitudinal axis of the airplane, and at least one wing attached to the fuselage between front and back ends of the fuselage and a substantially cylindrical central portion and a rear scaleable portion on which a vertical tail assembly and a rear propulsion assembly are attached. Between a section for connecting the rear portion to the central portion of the fuselage and the back end: the maximum width of each fuselage section is constant or increases towards the rear up to a maximum fuselage width L; the height of each fuselage section decreases towards the rear, such that the back end of the fuselage forms a thin trailing edge substantially horizontal in the indicating line of the airplane and substantially rectilinear; a reactor for the propulsion assembly is provided in a so-called semi-buried configuration in the fuselage. | ||||||
| 175 | 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 | US20110226894A1 | 2011-09-22 | 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. | ||||||
| 176 | REAR PART OF AN AIRCRAFT COMPRISING A STRUCTURE FOR SUPPORTING ENGINES, CONNECTED TO THE FUSELAGE BY AT LEAST ONE BLOCKING ELEMENT UNDER COMPRESSION LOADING | US13063080 | 2009-09-16 | US20110226893A1 | 2011-09-22 | Laurent Lafont; Frederic Journade |
| A rear part of an aircraft including a support structure for supporting engines, passing through the fuselage, through first and second openings. The rear part includes a connection structure connecting 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 first and second connection mechanisms each include at least one blocking element of the support structure, under compression loading by being applied to the casing and to the support structure. | ||||||
| 177 | METHODS AND SYSTEMS FOR MINIMIZING FLOW DISTURBANCES IN AIRCRAFT PROPELLER BLADES CAUSED BY UPSTREAM PYLONS | US12755711 | 2010-04-07 | US20110127374A1 | 2011-06-02 | Maria Caballero Asensio; Jorge Pablo Verde Preckler; Mats Gustavsson |
| Methods for minimizing the effects of pylori 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. | ||||||
| 178 | GAS TURBINE AIRCRAFT ENGINES AND OPERATION THEREOF | US12877493 | 2010-09-08 | US20110067412A1 | 2011-03-24 | Richard G. STRETTON |
| There is disclosed 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 so as to define part of an aerodynamic surface to the flow of ambient air, and a duct arrangement fluidly connecting the compressor to the heat exchanger. There is also proposed a method of operating the engine, the method involving the steps of: (a) flowing engine oil through the heat exchanger and thus into heat-exchange relationship with said ambient air; and (b) directing a bleed flow of compressor gas drawn from the compressor along said duct arrangement and into heat-exchange relationship with said oil in said heat exchanger, wherein said directing step (h) is performed selectively. | ||||||
| 179 | Supersonic aircraft jet engine | US11973813 | 2007-10-09 | US07837142B2 | 2010-11-23 | 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 x0) 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. | ||||||
| 180 | INVERTED AIRFOIL PYLON FOR AN AIRCRAFT | US12789306 | 2010-05-27 | US20100237187A1 | 2010-09-23 | 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. | ||||||
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