| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 101 | Multi-purpose aircraft | EP97109971.8 | 1994-08-24 | EP0798207A2 | 1997-10-01 | 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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| 102 | Aft engine for an aircraft | US14879217 | 2015-10-09 | US10017270B2 | 2018-07-10 | 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. | ||||||
| 103 | Aft engine for an aircraft | US14859523 | 2015-09-21 | US09957055B2 | 2018-05-01 | Patrick Michael Marrinan; Thomas Lee Becker; Kurt David Murrow |
| A propulsion system for an aircraft including a plurality of primary engines is provided. The plurality of primary engines includes at least a first primary engine and a second primary engine, each configured for mounting to a respective one of a pair of wings of the aircraft. The propulsion system additionally includes an aft engine configured for mounting at a tail section of the aircraft. The plurality of primary engines are sized to provide an amount of thrust sufficient for the aircraft to takeoff without use of the aft engine, such that the aft engine may be configured as a non-prime reliable engine. | ||||||
| 104 | Aircraft with electric propulsion means | US14304864 | 2014-06-13 | US09950801B2 | 2018-04-24 | 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. | ||||||
| 105 | NACELLE FOR AN AIRCRAFT AFT FAN | US15281990 | 2016-09-30 | US20180093776A1 | 2018-04-05 | Kishore Ramakrishnan; Patrick Michael Marrinan |
| An aircraft includes a fuselage extending between a forward end and an aft end. An aft engine is mounted to the aft end of the fuselage, the aft engine defining a centerline. The aft engine further includes a nacelle having a bottom section, the bottom section having a forward lip. The forward lip of the bottom section defines a camber line. The camber line, in turn, defines an angle relative to the centerline of the aft engine greater than or equal to at least about five degrees. | ||||||
| 106 | TILTROTOR PROPULSION SYSTEM FOR AN AIRCRAFT | US15259622 | 2016-09-08 | US20180065742A1 | 2018-03-08 | Randy M. Vondrell; Matthew Ryan Polakowski; Kurt David Murrow; Glenn Crabtree; Darek Tomasz Zatorski |
| An aircraft includes a fuselage and a wing assembly attached to or formed integrally with the fuselage. The aircraft also includes a propulsion system having a port propulsor and a starboard propulsor. The port and starboard propulsors are each attached to the wing assembly on opposing sides of the fuselage and are rotatable between a forward thrust position and a vertical thrust position. The propulsion system also includes a supplemental propulsor mounted to the fuselage to provide certain efficiencies for the aircraft. | ||||||
| 107 | AIRCRAFT PROPULSION UNIT COMPRISING AN UNDUCTED-FAN TURBINE ENGINE AND AN ATTACHMENT PYLON | US15551921 | 2016-02-18 | US20180065727A1 | 2018-03-08 | Mathieu Simon Paul GRUBER; Norman Bruno Andre JODET |
| A propulsion assembly for aircraft, the assembly including a turbojet having at least one unducted propulsion propeller; and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having an airfoil extending transversely between a leading edge and a trailing edge, the trailing edge of the airfoil of the pylon includes a cutout extending longitudinally over a fraction of the trailing edge facing at least a portion of the propeller, the cutout being configured to increase locally the distance between the trailing edge and the propeller, the cutout presenting an outline having a curved shape presenting at least two points of inflection. | ||||||
| 108 | NACELLE FOR AN AIRCRAFT AFT FAN | US15245286 | 2016-08-24 | US20180057181A1 | 2018-03-01 | Jixian Yao; Nikolai N. Pastouchenko; Ivan Malcevic |
| An aircraft is provided including a fuselage extending between a forward end and an aft end. An aft engine is mounted to the aft end of the fuselage and defines a centerline. The aft engine further includes a nacelle having a forward transition duct at the forward end of the nacelle. The forward transition duct also defines a centerline and the centerline of the forward transition duct is angled downward relative to the centerline of the aft engine. | ||||||
| 109 | AIRCRAFT HAVING AN AIRFLOW DUCT | US15208917 | 2016-07-13 | US20180016000A1 | 2018-01-18 | Nikolai N. Pastouchenko; Jixian Yao |
| An aircraft is provided including a propulsor having a plurality of fan blades. The aircraft additionally includes a fuselage, with the propulsor attached to the fuselage at an aft end of the fuselage. A stabilizer extends away from the fuselage proximate the aft end, the stabilizer including a portion positioned upstream of the plurality of fan blades. The aircraft additionally includes an airflow duct extending between an inlet and an outlet. The inlet is positioned to receive an airflow from a location outside the fuselage of the aircraft. The outlet is positioned to exhaust the airflow to at least partially offset a wake upstream of the plurality of fan blades, the wake generated by the stabilizer during operation of the aircraft. | ||||||
| 110 | PROPULSION ASSEMBLY FOR AN AIRCRAFT HAVING A TURBOJET WITH A NON-DUCTED FAN AND AN ATTACHMENT PYLON | US15182860 | 2016-06-15 | US20170088276A1 | 2017-03-30 | Mathieu Simon Paul GRUBER; Timothy DELTEIL Mc WILLIAMS |
| A propulsion assembly for an aircraft, the assembly including a turbojet having at least one unducted propulsive propeller, and an attachment pylon for attaching the turbojet to a structural element of the aircraft, the pylon being positioned on the turbojet upstream from the propeller and having a streamlined profile defined by two opposite side faces extending transversely between a leading edge and a trailing edge. The pylon includes a plurality of blow nozzles situated in the vicinity of its trailing edge and configured to blow air taken from a pressurized portion of the turbojet, the blow nozzles being positioned over at least a fraction of the trailing edge of the pylon that extends longitudinally facing at least a portion of the propeller. A method of reducing the noise generated by a pylon attaching a turbojet to an aircraft is presented. | ||||||
| 111 | NON-AXIS SYMMETRIC AFT ENGINE | US14859556 | 2015-09-21 | US20170081036A1 | 2017-03-23 | 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. | ||||||
| 112 | AFT ENGINE FOR AN AIRCRAFT | US14859523 | 2015-09-21 | US20170081034A1 | 2017-03-23 | Patrick Michael Marrinan; Thomas Lee Becker; Kurt David Murrow |
| A propulsion system for an aircraft including a plurality of primary engines is provided. The plurality of primary engines includes at least a first primary engine and a second primary engine, each configured for mounting to a respective one of a pair of wings of the aircraft. The propulsion system additionally includes an aft engine configured for mounting at a tail section of the aircraft. The plurality of primary engines are sized to provide an amount of thrust sufficient for the aircraft to takeoff without use of the aft engine, such that the aft engine may be configured as a non-prime reliable engine. | ||||||
| 113 | TRANSVERSE-MOUNTED POWER TURBINE DRIVE SYSTEM | US15104114 | 2014-12-12 | US20160290227A1 | 2016-10-06 | Wesley K. Lord |
| The present disclosure relates generally to an aircraft with counter-rotating pusher props powered by a gas turbine engine having a power turbine disposed substantially perpendicular to the compressor, combustor and turbine gas generator power core axis, as well as to the aircraft longitudinal axis. | ||||||
| 114 | ENGINE COWLING OF AN AIRCRAFT GAS TURBINE | US15087228 | 2016-03-31 | US20160288916A1 | 2016-10-06 | Predrag TODOROVIC |
| The invention relates to an engine cowling of an aircraft gas turbine which has a rear area that comprises at least two doors that are arranged at the bottom area of the rear area of the engine cowling and are to be opened by means of overhead hinges, wherein the hinges are arranged so as to be tilted with respect to the engine axis. | ||||||
| 115 | Engine installation | US14173394 | 2014-02-05 | US09346551B2 | 2016-05-24 | Richard Geoffrey Stretton |
| A fuselage mounted gas turbine engine installation the installation includes at least one propeller stage and a gas turbine core arranged in use to drive the propeller stage. The core is external to the fuselage and the rotational axes of the core and propeller stage are offset with respect to each other. | ||||||
| 116 | EMBEDDED ENGINES IN HYBRID BLENDED WING BODY | US14203735 | 2014-03-11 | US20160122005A1 | 2016-05-05 | Razvan Virgil Florea; William T. Cousins; Thomas G. Tillman; David J. Arend; John D. Wolter |
| A hybrid wing aircraft has an engine embedded into a body of the hybrid wing aircraft. The embedded engine has a fan that is received within a nacelle. The body of the aircraft provides a boundary layer over a circumferential portion of a fan. A system delivers additional air to correct fan stability issues raised by the boundary layer. | ||||||
| 117 | Aircraft Engine Mounting System | US14457287 | 2014-08-12 | US20160046381A1 | 2016-02-18 | 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. | ||||||
| 118 | Aircraft propulsion system and a method of controlling the same | US13584162 | 2012-08-13 | US09242721B2 | 2016-01-26 | Martin O. Neuteboom |
| An aircraft propulsion system has a propulsive rotor assembly rotatable about an axis of rotation and comprising a plurality of blades and a rotationally fixed vane assembly located adjacent to the propulsive rotor assembly and arranged circumferentially around the axis of rotation. As airflow enters the propulsive rotor assembly, a portion of the airflow passes over the vane assembly which is configured to direct the airflow away from the rotor blades so as to reduce the relative velocity of the redirected airflow over the rotor blades. This results in a reduced tendency of the airflow through the propulsive rotor assembly to become choked. | ||||||
| 119 | HYPERSONIC AIRCRAFT | US14099393 | 2013-12-06 | US20150108269A1 | 2015-04-23 | Richard H. Lugg |
| A supersonic aircraft having unique structural, geometrical, electromagnetic, mechanical, thermal and aerodynamic configuration is described. Its design characteristics maximize aerodynamic performance, speed, efficiency, comfort and range in the operational affect of carrying passengers over long distances at very high flight speeds and Mach numbers, generally above Mach 4.0+. It has fully integrated-mated fuselage twin engine nacelle structures which reduce and stabilize wave drag, wherein engines sit forward of the sonic boom electrode swept aerospace but are integrated right through the sub-wing, the aero-spike and inlet just above the top surface of the central wing, and above and the major wing mating join, attached via a massive composite titanium keel structure, through the central wing box and fuselage. | ||||||
| 120 | Air inlet of an aeroengine having unducted pusher propellers | US13128259 | 2009-11-09 | US08622340B2 | 2014-01-07 | Stephane Emmanuel Daniel Bensilum |
| An air intake for an aeroplane engine of type with unducted propellers, which intake can be connected by a pylon to a fuselage of an aeroplane, a local length of the air intake, measured parallel to the axis of the engine between a point on a leading edge of the air intake and a transverse plane situated at an inlet impeller of the engine compressor, is longer in a region of the air intake connected to the pylon and shorter in a region of the air intake opposite the pylon. | ||||||
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