| 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 | Supersonic aircraft jet engine | US11973813 | 2007-10-09 | US20090014597A1 | 2009-01-15 | 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. | ||||||
| 142 | Flight dynamics for an aircraft | US11644712 | 2006-12-22 | US20080149760A1 | 2008-06-26 | 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 Learjets are disclosed. 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. The inverted airfoil of the pylon negates an influence of the pylon on flight dynamics for improved overall flight dynamic 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 the fuselage, wherein the new location is aft of the original location. | ||||||
| 143 | Multi-purpose aircraft | US112877 | 1993-08-26 | US5645250A | 1997-07-08 | 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. | ||||||
| 144 | Aircraft nose mounting for jet engines | US18234350 | 1950-08-30 | US2685421A | 1954-08-03 | KLOSE ALFRED J |
| 145 | REVERSE CORE ENGINE WITH THRUST REVERSER | PCT/US2014023997 | 2014-03-12 | WO2014193515A3 | 2015-02-26 | SUCIU GABRIEL L; CHANDLER JESSE M |
| 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. | ||||||
| 146 | TWIN ENGINE AIRCRAFT | PCT/US9917316 | 1999-07-29 | WO0009392A3 | 2000-05-18 | WILLIAMS SAMUEL BARLOW |
| A jet aircraft (10) has a generally conical front fuselage section (14), a cylindrical intermediate fuselage section (16) defining a passenger compartment, a generally conical aft fuselage section (18), and a single vertical stabilizer (20). The aircraft's propulsion engines (30 and 32) are mounted on pylons (33) on the conical aft fuselage section (18) with the air inlets (34 and 36) thereof disposed entirely within a rearward projection (37) of the lateral cross section of the intermediate fuselage section (16) thereby to preclude the ingestion of foreign objects into the engines (30 and 32) while minimizing the effect of boundary layer airflow. The exhaust nozzles (50 and 52) extend rearwardly past the vertical stabilizer (20) to minimize side line noise. | ||||||
| 147 | A TURBINE ENGINE PROPELLED AIRPLANE HAVING AN ACOUSTIC BAFFLE | US15778415 | 2016-11-21 | US20180354634A1 | 2018-12-13 | Norman Bruno Andre JODET; Jeremy Paul Francisco GONZALEZ; Herve ROLLAND |
| An airplane propelled by a turbine engine having at least one fan, the turbine engine being integrated in the rear of a fuselage of the airplane, extending it rearwards, the airplane further including at least one acoustic baffle forming panel connected to the fuselage of the airplane and arranged below the turbine engine. | ||||||
| 148 | AIRCRAFT INCLUDING A STREAMLINED REAR THRUSTER WITH AN INPUT STATOR HAVING MOVABLE FLAPS | US15745691 | 2016-07-21 | US20180209445A1 | 2018-07-26 | Nicolas Jérôme Jean Tantot |
| An aircraft including a fuselage and a propulsion assembly. The propulsion assembly includes at least one fan rotor placed behind the fuselage as an extension thereof along a longitudinal axis, and a nacelle which forms a fairing of the at least one fan rotor through which at least one air flow passes. The aircraft comprises a plurality of stator radial arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle. The radial arms comprise at least one variable-pitch movable portion configured to axially divert the air flow. | ||||||
| 149 | NACELLE FOR AN AIRCRAFT AFT FAN | US15411228 | 2017-01-20 | US20180208297A1 | 2018-07-26 | Kishore Ramakrishnan; Trevor Howard Wood |
| An aircraft is provided including a fuselage extending between a forward end and an aft end. An aft engine is mounted to the fuselage at the aft end of the fuselage. The aft engine includes a nacelle having a forward section. An airflow duct is also provided extending at least partially through the nacelle and including an opening on the forward section of the nacelle. The opening is configured for providing an airflow to, or receiving an airflow from, the forward section of the nacelle to increase an amount of, e.g., boundary layer airflow received within the aft engine during operation of the aircraft, to guide the flow of boundary layer airflow into the engine more smoothly, or to reduce a distortion on the engine. | ||||||
| 150 | BOUNDARY LAYER INGESTION INTEGRATION | US15383104 | 2016-12-19 | US20180170560A1 | 2018-06-21 | ANGELINA M. CONTI; PATRICK G. HARVEY; KRUNAL B. MISTRY; KIMBERLY A. RINK; TED K. ROTHAUPT |
| Systems and methods for integrating Boundary Layer Ingestion (BLI) apparatus into an aircraft (1) are disclosed. The longerons (34) in the aft fuselage (18) may be extended to support an aft propulsor (20). The aft propulsor may be a turbofan or turboelectric propulsion system (46). An upper longeron (34a) may support a tail section (14) of an aircraft. The aft fuselage skin (22) is contoured to permit boundary layer airflow to enter an intake fan (24) of the aft propulsor. | ||||||
| 151 | Non-axisymmetric fixed or variable fan nozzle for boundary layer ingestion propulsion | US14295566 | 2014-06-04 | US09909530B2 | 2018-03-06 | Thomas G Tillman; Wesley K. Lord |
| A fan section for an engine has a fan which rotates about an axis, the fan has an inlet for ingesting ambient air, and a non-axisymmetric nozzle for providing the fan with non-uniform back pressure. | ||||||
| 152 | ROTORCRAFT WITH COWLING ABLE TO ROTATE AND TRANSLATE RELATIVE TO THE FUSELAGE | US15244379 | 2016-08-23 | US20180057183A1 | 2018-03-01 | Yann LE CADET; Christophe LETEURTRE |
| A rotorcraft comprising a cowling for closing an opening in the fuselage, the cowling being linked to the fuselage by means of a fastening system having a supporting means pivotally attached to the interior of the fuselage and a translation means coupled to the supporting means to respectively enable movements of rotation and translation of the cowling. | ||||||
| 153 | Non-axis symmetric aft engine | US14859556 | 2015-09-21 | US09884687B2 | 2018-02-06 | Patrick Michael Marrinan; Thomas Lee Becker; Kurt David Murrow; Jixian Yao |
| An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft. The aft engine includes a fan rotatable about a central axis of the aft engine, the fan including a plurality of fan blades. The aft engine also includes a nacelle surrounding the plurality of fan blades and defining an inlet. The inlet defines a non-axis symmetric shape with respect to the central axis of the aft engine to, e.g., allow for a maximum amount of airflow into the aft engine. | ||||||
| 154 | ASSEMBLY FOR AIRCRAFT COMPRISING ENGINES WITH BOUNDARY LAYER PROPULSION BY INJECTION | US15626698 | 2017-06-19 | US20170361939A1 | 2017-12-21 | Camil NEGULESCU; Jean-Michel ROGERO; Renaud FAURE |
| In order to further benefit from the principle of boundary layer ingestion by engines of an aircraft assembly, the rear portion of the fuselage of this aircraft assembly includes a front portion which splits up into at least two distinct rear portions, spaced apart from each other, and each integrating the rotary ring of the receiver of one of the engines. | ||||||
| 155 | DEVICE FOR REDUCING AERODYNAMIC DISTURBANCES IN THE WAKE OF AN AERODYNAMIC PROFILE BY VARIABLE-DISTRIBUTION BLOWING ON THE TOP SIDE AND THE UNDERSIDE | US15499230 | 2017-04-27 | US20170313412A1 | 2017-11-02 | Jerome COLMAGRO |
| A device for reducing aerodynamic disturbances in the wake of an aerodynamic profile. The device comprises a first air ejection nozzle arranged on the top side of the profile and a second air ejection nozzle arranged on the underside of the profile. A first blowing chamber is fluidically connected to the first nozzle and a second blowing chamber is fluidically connected to the second nozzle. Air supply means are configured to vary the distribution of air between said first blowing chamber and second blowing chamber. The distribution of the blown air can thus be adapted depending on the situation in which the profile is used, for example depending on the flight phase of an aircraft equipped with such a profile. Also, an aerodynamic profile, a pylon supporting a propulsion assembly for an aircraft comprising such an aerodynamic profile, and an aircraft. | ||||||
| 156 | Reverse core engine with thrust reverser | US14774896 | 2014-03-12 | US09719465B2 | 2017-08-01 | 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. | ||||||
| 157 | Air ejection device comprising an aerodynamic profile provided with a slot obturating flexible tongue | US14561488 | 2014-12-05 | US09656742B2 | 2017-05-23 | Julien Guillemaut; Arnaud Hormiere; Jerome Colmagro; Cesar Garnier |
| An air ejection device comprises an aerodynamic profile provided with a slot and an ejection nozzle. The device comprises a flexible tongue fixed flush with the aerodynamic profile in such a way as to obstruct the slot, the tongue being able to lift under the effect of a pressure differential between the air situated in the ejection nozzle and the outside air. The tongue makes it possible for the slot made in the profile to be obstructed during phases of flight during which the ejection of the air is unnecessary, and prevents external air from entering the slot. The flow of air over the aerodynamic profile is unaffected, and there is no increase in drag. Because the tongue lifts as a result of a pressure differential, it does not require any control mechanism to lift it. | ||||||
| 158 | AIRCRAFT WITH A PROPULSION UNIT COMPRISING A FAN AT THE REAR OF THE FUSELAGE | US15216626 | 2016-07-21 | US20170137137A1 | 2017-05-18 | Nils Edouard Romain BORDONI; Antoine Jean-Philippe BEAUJARD; Nicolas Jerome Jean TANTOT |
| The present invention relates to an aircraft comprising a fuselage (1) and a propulsion unit at the rear of the fuselage, the propulsion unit comprising at least one fan rotor (7, 8), a nacelle (14) fairing the fan and at least one connection means (15) connecting the nacelle to the fuselage, the fan being rotated by the energy supplied by at least one gas-turbine gas generator (2a, 2b) housed in the fuselage, said gas generator comprising auxiliary equipment cooled by a cooling circuit.The aircraft is characterised in that said cooling circuit comprises at least one heat exchanger exchanging heat with the ambient air housed in one of said connection means (15) and/or in said nacelle (14). The cooling circuit optionally comprises also a heat exchanger exchanging heat with the ambient air, housed in the tail unit. | ||||||
| 159 | METAL AND COMPOSITE LEADING EDGE ASSEMBLIES | US14929058 | 2015-10-30 | US20170127477A1 | 2017-05-04 | A. David Sandiford |
| Various components and methods related to a leading edge assembly are disclosed. The leading edge assembly can include an outer strike shell and a foam core. The foam core can be located inside the outer strike shell. The leading edge assembly can include a heating element with a plurality of sensors and wires. A method of manufacturing a leading edge assembly can include forming a composite layer, applying a metallic layer to the composite layer, installing an electronic device, and inserting a foam core into a cavity bounded by the composite layer and/or the electronic device. | ||||||
| 160 | AFT ENGINE FOR AN AIRCRAFT | US14879217 | 2015-10-09 | US20170101191A1 | 2017-04-13 | 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 attached to a fan shaft. The aft engine also includes a nacelle encircling the plurality of fan blades and a structural support system for mounting the aft engine to the aircraft. The structural support system extends from the fuselage of the aircraft, through the fan shaft, and to the nacelle 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. | ||||||
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