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公开(公告)号：US20180334259A1
公开(公告)日：2018-11-22
申请号：US15981054
申请日：2018-05-16
申请人： Rohr, Inc.
发明人： Michael Aten , Anthony Lacko
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/264
摘要： An assembly is provided for an aircraft. This aircraft assembly includes an aircraft propulsion system and a pylon configured to mount the aircraft propulsion system to an airframe member. The pylon includes a first pylon structure and a second pylon structure. The first pylon structure is configured to mount to the airframe member. The second pylon structure is mounted to the aircraft propulsion system. The second pylon structure is configured to disconnect from the first pylon structure while mounted to the airframe member.
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2.发明申请公开(公告)号：US20180305032A1
公开(公告)日：2018-10-25
申请号：US15956154
申请日：2018-04-18
发明人： Guillaume GALLANT , Olivier GLEIZE
CPC分类号： B64D27/26 , B64D27/12 , B64D27/18 , B64D2027/266 , F02C7/20
摘要： An engine assembly for an aircraft, comprising an engine mounting pylon comprising a primary structure forming a box closed by a front closing rib, a front engine mount comprising at least two connecting link rods that are disposed laterally on either side of the box and each comprise a first end mounted on a first fitting of the casing. The rib forms a part of the front mount, comprising at least one transverse fitting made in one piece so as to close a front end of the box and to have lugs protruding laterally on each side of the box, each lug being provided with a first orifice for mounting a second end of one of the link rods.
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公开(公告)号：US20180238186A1
公开(公告)日：2018-08-23
申请号：US15439122
申请日：2017-02-22
发明人： Brandon Wayne Miller , Thomas Ory Moniz , Monty Lee Shelton , Joel Francis Kirk , Jeffrey Donald Clements
CPC分类号： B64D27/10 , B64D27/18 , F02C7/20 , F02K3/06 , F05D2250/323 , F05D2250/52 , F05D2250/712 , Y02T50/672
摘要： The present disclosure is directed to a gas turbine engine defining a radial direction, a longitudinal direction, and a circumferential direction, an upstream end and a downstream end along the longitudinal direction, and an axial centerline extended along the longitudinal direction. The gas turbine engine includes a low pressure (LP) turbine defining an outer flowpath. The outer flowpath defines a first outer flowpath radius at an upstream-most end of the LP turbine, a last outer flowpath radius disposed at a downstream-most end of the LP turbine, a middle outer flowpath radius disposed therebetween along the longitudinal direction. The middle outer flowpath radius is greater than the last outer flowpath radius.
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公开(公告)号：US10017270B2
公开(公告)日：2018-07-10
申请号：US14879217
申请日：2015-10-09
IPC分类号： B64D33/02 , B64D27/18 , B64D27/24 , B64D27/26 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/32 , F04D29/36 , F04D29/52 , F04D29/54 , B64C1/16 , B64C21/06 , B64D27/20 , B64D29/04 , B64D27/02
CPC分类号： B64D33/02 , B64C1/16 , B64C21/06 , B64D27/18 , B64D27/20 , B64D27/24 , B64D27/26 , B64D29/04 , B64D2027/026 , B64D2033/0226 , F01D15/10 , F02C7/32 , F02K3/062 , F04D29/325 , F04D29/36 , F04D29/522 , F04D29/542 , F05D2220/323 , Y02T50/166
摘要： 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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公开(公告)号：US20180170562A1
公开(公告)日：2018-06-21
申请号：US15892334
申请日：2018-02-08
申请人： The Boeing Company
发明人： Omid B. Nakhjavani , Robert H. Willie , Paul S. Park , Mohammad Ali Heidari , Leonard J. Hebert , Milan Stefanovic , Parminder Singh , Naimishkumar B. Harpal , Andrew Y. Na
CPC分类号： B64D27/18 , B64D27/26 , B64D2027/264 , Y02T50/44
摘要： In one example, a strut for mounting a jet engine to a wing of an aircraft includes a plurality of engine mounts and a space frame truss supported from the wing and including front and aft portions, the front portion being coupled to and supporting the engine mounts, the aft portion extending upwardly and rearwardly from an aft end of the front portion. By removing the aft end of the strut from the core exhaust zone of the engine, substantial reductions in the weight and drag of the strut, and a corresponding increase in the specific fuel consumption of the associated aircraft may be achieved.
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公开(公告)号：US09970322B2
公开(公告)日：2018-05-15
申请号：US14759986
申请日：2014-03-11
发明人： Gabriel L. Suciu , Brian D. Merry
CPC分类号： F01D25/162 , B64D27/18 , B64D2027/264 , F01D25/28 , F02C7/20 , Y02T50/44 , Y02T50/671
摘要： A mounting system for a gas turbine engine includes a low pressure turbine section, a first bearing, a mid-turbine frame, and a rear mount. The first bearing supports at least a portion of the low pressure turbine section. The mid-turbine frame supports the first bearing. The rear mount is connected to the mid-turbine frame and is configured to react loads from the gas turbine engine.
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公开(公告)号：US20180127089A1
公开(公告)日：2018-05-10
申请号：US15343847
申请日：2016-11-04
申请人： U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration
发明人： Jason R. Welstead , James L. Felder
CPC分类号： B64C21/06 , B60L50/16 , B60L2200/10 , B64C1/16 , B64D27/18 , B64D27/24 , B64D2027/026 , B64D2221/00 , Y02T10/70 , Y02T10/7077
摘要： A turboelectric vehicle may include a fuselage and a wing coupled to the fuselage. A wing propulsor may be coupled to the wing. A rear propulsor may be positioned at a rear portion of the fuselage and may be electrically coupled to the wing propulsor. The rear propulsor may be configured to receive power extracted from the wing propulsor.
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公开(公告)号：US09963999B2
公开(公告)日：2018-05-08
申请号：US15386954
申请日：2016-12-21
申请人： SAFRAN NACELLES
摘要： The disclosure relates to an aircraft propulsion assembly comprising a bypass turbojet engine equipped with a nacelle, the bypass turbojet engine including a structure defining a first part of a secondary flow path for channeling secondary flow, and the nacelle having a structure defining a second part of the secondary flow path. The structure of the nacelle defining the second part of the secondary flow path is arranged such that the first part and the second part of the secondary flow path are angularly offset around a longitudinal axis of the engine when the engine is shut down/stopped.
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公开(公告)号：US20180119640A1
公开(公告)日：2018-05-03
申请号：US15342694
申请日：2016-11-03
申请人： THE BOEING COMPANY
发明人： Sean P. HOWE
IPC分类号： F02K1/18 , B64D33/04 , B64D27/18 , B64D31/06 , F02K1/82 , F04D29/52 , F04D29/54 , F01D25/24 , F04D27/00
CPC分类号： F02K1/18 , B64D27/18 , B64D31/06 , B64D33/04 , F01D25/24 , F02K1/00 , F02K1/12 , F02K1/15 , F02K1/30 , F02K1/70 , F02K1/82 , F04D27/001 , F04D29/522 , F04D29/545 , F05D2220/323 , F05D2250/324 , F05D2270/3015
摘要： A fan nacelle, a gas turbine engine cell assembly, and an aircraft are provided. The fan nacelle includes a fan duct skin arranged in a fan duct to direct airflow from the fan of a Turbofan engine toward a fan nozzle. An exterior skin of the fan nacelle directs air flow around an exterior of the engine. The fan duct skin and the exterior skin terminate at a trailing edge, and a trailing edge portion of the exterior skin is one of parallel to and diverging from a trailing edge portion of the fan duct skin in an aft direction. In certain aspects, the trailing edge portion of the exterior skin is actuatable or inflatable to selectively divert from the trailing edge portion of the fan duct skin.
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公开(公告)号：US09856031B2
公开(公告)日：2018-01-02
申请号：US14614650
申请日：2015-02-05
发明人： Jingo Tateiwa
CPC分类号： B64D29/02 , B64D27/18 , F02C7/20 , F02C7/266 , F05D2240/91 , F05D2250/30 , Y02T50/44 , Y02T50/671
摘要： An aircraft with a turbofan engine including an engine body and a fan, wherein the turbofan engine is supported on an airframe via a pylon, an igniter cable is interposed between an ignition plug of the engine and an ignition control unit that controls power supply to the ignition plug, and at least a part of the igniter cable is passed through an inside of the pylon.
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