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公开(公告)号：US11668265B2
公开(公告)日：2023-06-06
申请号：US17479384
申请日：2021-09-20
申请人： Rohr, Inc.
发明人： Jennifer Davis
CPC分类号： F02K1/72 , B29C53/24 , B29C66/43 , B29C66/721 , B29C70/46 , F02K1/54 , B29K2701/12 , B29L2031/3076
摘要： A manufacturing process is provided during which a thrust reverser cascade is formed for an aircraft propulsion system. During the formation of the thrust reverser cascade, a first panel of material is stamped into a first corrugated body. A second panel of material is stamped into a second corrugated body. The first corrugated body is bonded to the second corrugated body.
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公开(公告)号：US20220176614A1
公开(公告)日：2022-06-09
申请号：US17479384
申请日：2021-09-20
申请人： Rohr, Inc.
发明人： Jennifer Davis
摘要： A manufacturing process is provided during which a thrust reverser cascade is formed for an aircraft propulsion system. During the formation of the thrust reverser cascade, a first panel of material is stamped into a first corrugated body. A second panel of material is stamped into a second corrugated body. The first corrugated body is bonded to the second corrugated body.
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公开(公告)号：US10823112B2
公开(公告)日：2020-11-03
申请号：US15605120
申请日：2017-05-25
申请人： THE BOEING COMPANY
摘要： A method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.
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公开(公告)号：US20200291893A1
公开(公告)日：2020-09-17
申请号：US16785117
申请日：2020-02-07
申请人： SAFRAN , Safran Nacelles
摘要： A thrust reverser cascade for an aircraft nacelle includes a plurality of blades having a first and a second surface, the blades being connected to members connected to attachment flanges for attaching the thrust reverser cascade to the nacelle. At least one of the surfaces of the blades is covered with at least one layer of fibers, each layer including a plurality of fiber pieces which are pre-impregnated with resin. The fiber pieces are superimposed on one another, positioned parallel to the aerodynamic surface of the blade and oriented in different directions.
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公开(公告)号：US20190242273A1
公开(公告)日：2019-08-08
申请号：US16384778
申请日：2019-04-15
CPC分类号： F01D25/285 , B64F5/50 , F02K1/54 , F05D2220/323 , Y10T29/49998
摘要： A rack for holding a portion of a thrust reverser. The rack may include a base and a supporting frame disposed perpendicularly with the base. The base and the supporting frame may include a hinge at each location where the base and the supporting frame are coupled together. The rack may also include two supporting poles parallel to the supporting frame. The two supporting poles may be designed such that the portion of the thrust reverser may be mounted onto the two supporting poles.
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公开(公告)号：US10309434B2
公开(公告)日：2019-06-04
申请号：US15087531
申请日：2016-03-31
申请人： The Boeing Company
IPC分类号： F16B5/01 , F01D25/24 , F02K1/54 , F16B5/02 , F02C7/20 , B64D27/12 , B64D29/06 , F02K1/60 , F02K1/76
摘要： Provided is an aircraft propulsor thrust reverser with a fastening system. The fastening system may include a male spool and a female spool configured to be threaded into the male spool. The male spool and the female spool may be coupled to a honeycomb structure and may evenly distribute force to the honeycomb structure to prevent plastic deformation of a honeycomb core of the honeycomb structure.
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公开(公告)号：US20180340492A1
公开(公告)日：2018-11-29
申请号：US15605120
申请日：2017-05-25
申请人： THE BOEING COMPANY
IPC分类号： F02K1/54
CPC分类号： F02K1/54 , F02K1/64 , F02K1/72 , F05D2230/51 , F05D2230/60 , F05D2240/129 , F05D2240/40
摘要： A method for manufacturing a cascade for a thrust reverser for a jet engine includes forming a strip assembly. The strip assembly includes a strong back member which includes a length. The strip assembly includes a plurality of first vane members which extend from a first side of the strong back member in a first direction nonparallel relative to the length of strong back member wherein the plurality of the first vane members are spaced apart from one another along the length of the strong back member.
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公开(公告)号：US09989010B2
公开(公告)日：2018-06-05
申请号：US14959384
申请日：2015-12-04
发明人： Loic Dussol , Jerome Dane , Hugo Herisson
CPC分类号： F02K1/827 , F02K1/72 , F05D2250/283 , F05D2260/963 , Y02T50/671
摘要： A thrust reverser for an aircraft engine assembly, comprising two sub-assemblies configured to surround an engine, each of the sub-assemblies comprising an inner fixed structure, a translating cowl, a torque box, a substantially vertical 12 o'clock bifurcation, and a substantially vertical 6 o'clock bifurcation. At least one of the sub-assemblies comprises at least one separating partition extending between the inner fixed structure, the translating cowl and the torque box of the sub-assembly, the separating partition being rigidly fixed to the inner fixed structure and the torque box, and connected to the translating cowl via a sliding connection.
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公开(公告)号：US09868514B2
公开(公告)日：2018-01-16
申请号：US14455071
申请日：2014-08-08
CPC分类号： B64C13/28 , B64C9/18 , B64D45/00 , B64D2045/001 , B64D2045/0085 , F02K1/54
摘要： The invention relates to a flap system for an aircraft high lift system or an engine actuation with a rotary shaft system, one or more drive stations as well as elements for transmitting the drive energy from the rotary shaft system to the one or more drive stations, wherein at least one drive station includes at least two independent load paths with at least one rotational transmission each for actuating the flap kinematics, and per load path at least one mechanically coupling-free synchronization unit is provided for compensating regular load fluctuations between the load paths. The invention furthermore relates to a method for monitoring a flap system with at least two redundant load paths which each comprise at least one rotational transmission, wherein it is cyclically checked whether the difference of the output-side torques of the at least two load paths exceeds a defined threshold value and/or lies within a defined limit range.
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公开(公告)号：US09771863B2
公开(公告)日：2017-09-26
申请号：US14600304
申请日：2015-01-20
摘要： An aircraft body comprises a support structure. A gas turbine engine comprises a gas generator having at least one compressor rotor, at least one gas generator turbine rotor, and a combustion section. A fan drive turbine is positioned downstream of at least one gas generator turbine rotor, and is configured to drive a shaft. The shaft engages gears to drive a plurality of fan rotors. The gas turbine engine is embedded into the support structure such that there is an inlet leading through the support structure to the fan rotors to deliver air to the fan rotors. A gas turbine engine is also disclosed.
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