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公开(公告)号：US11639700B2
公开(公告)日：2023-05-02
申请号：US17014884
申请日：2020-09-08
发明人： Michael Kevin Smart
摘要： Airframe integrated scramjet engines are disclosed. Scramjet engines within the scope of this disclosure may be configured to integrate smoothly with an airframe of a hypersonic flight aircraft or vehicle. The scramjet engine may include capture shape of an inlet configured to capture airflow, a combustor configured for combustion of fuel and air, and an exit shape of a nozzle configured for expansion of the combusted fuel and air to provide hypersonic thrust. In some embodiments, the scramjet engine has a fixed geometry and a transitioning cross-sectional shape over its full length. The scramjet engine is configured to be a component of launch vehicle system.
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公开(公告)号：US11639686B2
公开(公告)日：2023-05-02
申请号：US17159343
申请日：2021-01-27
申请人： Rohr, Inc.
发明人： Timothy Gormley
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a center body, a scarfed inlet structure and an inlet passage. The scarfed inlet structure extends circumferentially about the center body. The inlet passage is radially between and formed by at least the center body and the scarfed inlet structure. A first component of the assembly is configured to rotate about an axis relative to a second component of the assembly between: (A) a first position where a metering portion of the inlet passage has a first area; and (B) a second position where the metering portion has a second area. The first component is one of the center body or the scarfed inlet structure, and the second component is the other one of the center body or the scarfed inlet structure.
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公开(公告)号：US11638972B2
公开(公告)日：2023-05-02
申请号：US16841973
申请日：2020-04-07
发明人： Florian Ravise , Florent Mercat
IPC分类号： B23K26/38 , B23K26/382 , F02C7/045 , B23K101/00 , B23K103/16 , B64D33/02
摘要： A method for manufacturing a porous layer of an acoustic attenuation structure, porous layer of an acoustic attenuation structure thus obtained and acoustic attenuation structure comprising the porous layer. A method for manufacturing a porous layer of an acoustic attenuation structure includes a first step of production of a solid layer including at least one structural frame embedded in a resin matrix and having first and second reinforcing strips arranged so as to delimit zones without reinforcing strips and a second step of production of through-holes in the zones without reinforcing strips of the solid layer using a laser beam.
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公开(公告)号：US11628924B2
公开(公告)日：2023-04-18
申请号：US16946121
申请日：2020-06-06
申请人： Pierce Osborn
发明人： Pierce Osborn
IPC分类号： B64C13/04 , B64D33/02 , B64C31/036
摘要： The invention described and claimed in this application is a throttle assembly for a paramotor with an integrated locking mechanism which can be engaged to lock the throttle input in any position to maintain level flight. The throttle locking mechanism can be quickly disengaged as needed by squeezing the throttle control lever. The throttle locking mechanism is also able to be tuned when in the locked position as to attain the ideal engine input for level flight. The throttle locking mechanism can be preset and quickly returned to a designated power setting.
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公开(公告)号：US11623753B2
公开(公告)日：2023-04-11
申请号：US16595771
申请日：2019-10-08
申请人： Goodrich Corporation
发明人： Nathaniel Ching , Jin Hu , Peter J. Walsh , Casey Slane
IPC分类号： B64D15/12 , C09J7/38 , C08K3/08 , C09J9/02 , C09J11/04 , B64D15/00 , C09J5/06 , C08K3/22 , B82Y30/00 , B64D33/02 , C09J9/00 , C09J109/02 , C09J175/04 , C09J123/08
摘要： A method of making an adhesive for an ice protection assembly includes mixing ferrous nanoparticles into the adhesive. Removal of the adhesive for ice protection assembly inspection or repair includes heating the ferrous nanoparticles in the adhesive to soften the adhesive and allow for easy removal or repositioning of the ice protection assembly.
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公开(公告)号：US11614051B2
公开(公告)日：2023-03-28
申请号：US17600539
申请日：2020-04-08
摘要： Disclosed is a method for using an aircraft turbojet engine comprising an air inlet comprising a plurality of rectifier vanes, each rectifier vane being mounted such that it can move between a retracted position to assist the thrust phase and a deployed position in which the rectifier vane protrudes from the inner wall in a radially inward direction in order to rectify the reverse air flow of the inner wall to assist a thrust-reverse phase, in which method at least one rectifier vane is in the retracted position during a turbojet engine thrust phase, the method comprising, during a thrust-reverse phase of the turbojet engine, a step of moving the rectifier vane to the deployed position.
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公开(公告)号：US11608782B2
公开(公告)日：2023-03-21
申请号：US16849364
申请日：2020-04-15
摘要： An inertial particle separator (IPS) for a gas turbine engine, has: inner and outer walls extending about a central axis, an inlet defined between the inner and outer walls and oriented axially; swirling vanes extending at least radially between the inner and outer walls and circumferentially distributed around the central axis, the swirling vanes configured for inducing a circumferential component in an airflow flowing between the swirling vanes; a plenum between the inner and outer walls downstream of the swirling vanes, the plenum circumferentially extending about the central axis, the outer wall converging toward the central axis in a direction of the airflow; and a splitter radially between the inner and outer walls downstream of the plenum and circumferentially extending around the central axis, a particle outlet radially between the splitter and the outer wall, an air outlet radially between the inner wall and the splitter.
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公开(公告)号：US20230080020A1
公开(公告)日：2023-03-16
申请号：US17472120
申请日：2021-09-10
申请人： Rohr, Inc.
摘要： An assembly is provided for an aircraft propulsion system. This assembly includes a variable area inlet. The variable area inlet includes a moveable structure configured to move axially along an axial centerline between a first position and a second position. The variable area inlet is configured to open an airflow inlet passage into the aircraft propulsion system when the movable structure is in the first position. The variable area inlet is configured to close the airflow inlet passage when the movable structure is in the second position. The airflow inlet passage includes an inlet. The inlet extends axially along the axial centerline from a first end to a second end. A distance from the first end to the second end changes as the inlet extends laterally between a first side and a second side.
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公开(公告)号：US11598214B2
公开(公告)日：2023-03-07
申请号：US17412759
申请日：2021-08-26
申请人： ROLLS-ROYCE plc
摘要： An aircraft engine comprising a fan, the fan having a diameter D and including a plurality of fan blades, the fan blades having a sweep metric S, each fan blade having a leading edge, and a forward-most portion on the leading edge of each fan blade being in a first reference plane. The aircraft engine further comprises a nacelle, comprising an intake portion forward of the fan, a forward edge on the intake portion being in a second reference plane, wherein the intake portion has a length L measured along an axis of the aircraft engine between the first reference plane and the second reference plane, the aircraft engine having a cruise design point condition Mrel, wherein Mrel is between 0.4 and 0.93, and L/D is between 0.2 and 0.45.
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公开(公告)号：US11591101B2
公开(公告)日：2023-02-28
申请号：US16743966
申请日：2020-01-15
摘要： A diffuser may comprise an inlet and an outlet. The inlet may comprise an arcuate shape. The outlet may comprise an annular shape. The diffuser may transition from the arcuate shape at the inlet to the annular shape at the outlet. The diffuser may comprise a radially inner wall and a radially outer wall disposed opposite the radially inner wall. The radially inner wall and the radially outer wall may partially define a duct.
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