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51. 发明授权

US3742711A Modulatable thrust nozzle apparatus 失效
标题翻译：可调节喷嘴装置
公开(公告)号：US3742711A
公开(公告)日：1973-07-03
申请号：US3742711D
申请日：1972-02-07
申请人： ROHR INDUSTRIES INC
发明人： TIMMS R
IPC分类号： F02K1/36 , F02K1/38 , F02K3/04 , F02K1/02
CPC分类号： F02K1/36 , F02K1/383
摘要： Fan jet engine has cowl surrounding engine and terminating in jet exhaust nozzle. Elongate shroud surrounds fan and engine to define annular passage for fan air and terminates forward of exit end of exhaust nozzle. Aft portion of shroud is separate sleeve movable axially rearward to define peripheral gap for inflow of free stream air to add to mass delivered by fan. Engine cowl converges rearwardly from transverse plane of aft end of sleeve. When sleeve is stowed it defines with the cowl a convergent nozzle of minimum discharge area. When it is fully deployed, it forms with the cowl a divergent nozzle of maximum discharge area conformed to produce optimum thrust for takeoff.
摘要翻译：风机喷气发动机具有整流罩周围发动机，并终止喷气排气喷嘴。细长的护罩围绕风扇和发动机，以定义用于风扇空气的环形通道，并在排气喷嘴出口端的前方终止。护罩的后部分是可以轴向向后移动的独立套筒，以限定用于自由流空气流入的外围间隙，以增加由风扇输送的质量。发动机罩从套筒后端的横向平面向后收敛。当套管被收起时，其与整流罩一起形成具有最小排放面积的会聚喷嘴。当其完全展开时，其与整流罩形成最大排放面积的发散喷嘴符合产生用于起飞的最佳推力。

52. 发明授权

US3615052A Variable area exhaust nozzle 失效
标题翻译：可变区域排气喷嘴
公开(公告)号：US3615052A
公开(公告)日：1971-10-26
申请号：US3615052D
申请日：1968-10-17
申请人： UNITED AIRCRAFT CORP
发明人： TUMAVICUS JULIUS W
IPC分类号： F02K1/00 , F02K1/10 , F02K1/38 , F02K1/40 , B64C15/06
CPC分类号： F02K1/383 , F02K1/006 , F02K1/10 , F02K1/40
摘要： A VARIABLE AREA EXHAUST NOZZLE FOR A THRUST GENERATING ENGINE WHICH INCLUDES AN EXHAUST DUCT MEMBER WITH FIXED SIDE WALLS AND WITH A PLURALITY OF PIVOTABLE FLAPS ATTACHED THERETO AND COOPERATING THEREWITH TO DEFINE A HIGH ASPECT RATIO EXHAUST NOZZLE WHEN THE FLAPS ARE PIVOTED INWARDLY TO THEIR MINIMUM AREA POSITION AND A LOW ASPECT RATIO EXHAUST NOZZLE WHEN THE FLAPS ARE PIVOTED OUTWARDLY TO THEIR MAXIMUM AREA POSITION.

53. 发明授权

US3613826A System for reducing noise caused by a stream of fluid 失效
标题翻译：用于减少由流体流引起的噪声的系统
公开(公告)号：US3613826A
公开(公告)日：1971-10-19
申请号：US3613826D
申请日：1970-06-25
申请人： BERTIN & CIE
发明人： CABASSUT ANDRE EMILE ROGER
IPC分类号： F02K1/38 , B64D33/06
CPC分类号： F02K1/383 , Y02T50/671
摘要： A system for reducing noise caused by a stream of fluid comprises a fluid ejection conduit comprising two series of ambient fluid intake vents distributed around its periphery; and Two series of orientatable tubular elements respectively connected to the said vents and arranged to occupy two positions, namely a retracted position in which they are folded back adjacent the inner wall of the conduit and form along the latter a substantially continuous ring bounding a continuous passage for the stream of fluid, and a noise-attenuating position in which the said tubular elements extend obliquely rearwardly and towards the axis of the conduit, the elements of the first series abutting one another at their free end in the noise-attenuating position so as to form a substantially continuous outlet ring for the ambient fluid, while the elements of the second series in the noise-attenuating position lead into the conduit at different distances from the axis of the latter as compared to the distances of the conduits of the other series in the noiseattenuating position.

54. 发明授权

US3391898A Actuating mechanism 失效
标题翻译：执行机制
公开(公告)号：US3391898A
公开(公告)日：1968-07-09
申请号：US51729765
申请日：1965-12-29
申请人： UNITED AIRCRAFT CORP
发明人： MILLER GUY W
IPC分类号： B64D27/02 , F02K1/12 , F02K1/38
CPC分类号： B64D27/023 , F02K1/123 , F02K1/383

55. 发明授权

US2987879A Jet propulsion nozzle with noise reducing means 失效
标题翻译：喷气推进喷嘴采用降噪装置
公开(公告)号：US2987879A
公开(公告)日：1961-06-13
申请号：US69098657
申请日：1957-10-18
申请人： ROLLS ROYCE
发明人： MORRIS BROWN DAVID
IPC分类号： F02K1/08 , F02K1/38 , F02K1/60
CPC分类号： F02K1/08 , F02K1/383 , F02K1/60

56. 发明申请

US20160084199A1 JET EXHAUST NOISE REDUCTION 审中-公开
标题翻译：喷气式排气噪声减少
公开(公告)号：US20160084199A1
公开(公告)日：2016-03-24
申请号：US14959441
申请日：2015-12-04
申请人： LOCKHEED MARTIN CORPORATION
发明人： Neal D. Domel , Daniel N. Miller
IPC分类号： F02K1/34
CPC分类号： F02K1/34 , F02K1/383
摘要： Reducing jet noise by weakening Mach cones in a jet exhaust gas streamtube. The Mach cones are weakened by modifying exhaust gas flow in a longitudinal axial core of the exhaust gas streamtube.
摘要翻译：通过在喷气式排气流管中减弱马赫锥来减少喷气噪音。通过改变废气流管的纵向轴向芯中的废气流来减弱马赫锥。

57. 发明申请

US20150121841A1 FLOW CONTROL DEVICE FOR A THREE STREAM TURBOFAN ENGINE 审中-公开
标题翻译：三流涡轮发动机的流量控制装置
公开(公告)号：US20150121841A1
公开(公告)日：2015-05-07
申请号：US14206232
申请日：2014-03-12
申请人： United Technologies Corporation
发明人： Felix Izquierdo , Robert H. Bush , Timothy J. McAlice
IPC分类号： F02K3/075 , F02K3/077
CPC分类号： F02K3/075 , F02K1/08 , F02K1/28 , F02K1/383 , F02K1/46 , F02K3/077 , F05D2270/051
摘要： A gas turbine engine includes a core engine, a first bypass passage disposed about the core engine and a second bypass passage disposed about the first bypass passage. A flow control is disposed within the second bypass for controlling bypass airflow through the second bypass. The flow control translates axially between an open position and a closed position to vary and control airflow through the second bypass passage.
摘要翻译：燃气涡轮发动机包括核心发动机，围绕核心发动机设置的第一旁路通道和围绕第一旁路通道设置的第二旁路通道。流量控制器设置在第二旁路内用于控制通过第二旁路的旁路气流。流量控制在打开位置和关闭位置之间轴向平移以改变和控制通过第二旁路通道的气流。

58. 发明申请

US20140263712A1 EXHAUST NOZZLE APPARATUS AND METHOD FOR MULTI STREAM AIRCRAFT ENGINE 有权
标题翻译：用于多流航空发动机的排气喷嘴装置和方法
公开(公告)号：US20140263712A1
公开(公告)日：2014-09-18
申请号：US14202534
申请日：2014-03-10
申请人： Rolls-Royce North American Technologies, Inc.
发明人： Kenneth W. Froemming , Bryan H. Lerg
IPC分类号： F02K1/30
CPC分类号： F02K1/383 , F02K1/30 , F02K1/36 , F02K3/077 , Y02T50/672
摘要： A multi stream aircraft fixed geometry nozzle includes an inner nozzle, an outer nozzle, and a supersonic ejector. The outer nozzle is configured to channel a third stream from an aft end of a third stream duct surrounding a bypass duct of a multi stream aircraft engine to the supersonic ejector to merge the third stream with the primary stream. The fixed geometry nozzle is configured to operate between an SFC mode and a thrust mode such that, when the inner nozzle accelerates the primary stream supersonically to the supersonic ejector, at which the primary stream is merged with the third stream, in the SFC mode the total pressure of the primary stream is substantially the same as the total pressure of the third stream, and in the thrust mode the total pressure of the primary stream is substantially greater than the total pressure of the third stream.
摘要翻译：多流飞机固定几何喷嘴包括内喷嘴，外喷嘴和超音速喷射器。外喷嘴构造成将第三流从第三流管的后端引导到多流喷气发动机的旁路管道，以将第三流与主流合并。固定几何喷嘴构造成在SFC模式和推力模式之间操作，使得当内喷嘴将主流加速到超音速喷射器时，主流与第三流合并，在SFC模式中主流的总压力基本上与第三流的总压力相同，并且在推力模式中，主流的总压力基本上大于第三流的总压力。

59. 发明申请

US20120104161A1 VARIABLE GEOMETRY AIRCRAFT PYLON STRUCTURE AND RELATED OPERATION TECHNIQUES 有权
标题翻译：可变几何飞机PYLON结构及相关操作技术
公开(公告)号：US20120104161A1
公开(公告)日：2012-05-03
申请号：US13211171
申请日：2011-08-16
申请人： Parthiv N. Shah
发明人： Parthiv N. Shah
IPC分类号： B64C15/02 , B64C9/38
CPC分类号： B64C9/36 , B64C7/02 , B64D27/18 , B64D33/04 , F02K1/12 , F02K1/383
摘要： An aircraft control structure can be utilized for purposes of drag management, noise control, or aircraft flight maneuvering. The control structure includes a high pressure engine nozzle, such as a bypass nozzle or a core nozzle of a turbofan engine. The nozzle exhausts a high pressure fluid stream, which can be swirled using a deployable swirl vane architecture. The control structure also includes a variable geometry pylon configured to be coupled between the nozzle and the aircraft. The variable geometry pylon has a moveable pylon section that can be deployed into a deflected state to maintain or alter a swirling fluid stream (when the swirl vane architecture is deployed) for drag management purposes, or to assist in the performance of aircraft flight maneuvers.
摘要翻译：飞机控制结构可用于拖曳管理，噪声控制或飞行器飞行操纵的目的。控制结构包括高压发动机喷嘴，例如涡轮风扇发动机的旁路喷嘴或核心喷嘴。喷嘴排出高压流体流，其可以使用可部署的旋流叶片结构旋转。控制结构还包括可变几何挂架，其构造成联接在喷嘴和飞行器之间。可变几何塔具有可移动的塔架部分，其可以部署到偏转状态以维持或改变旋流流体流（当旋涡叶片结构部署时）用于拖曳管理目的，或者协助执行飞行器飞行机动。

60. 发明申请

US20120067025A1 BLOOM MIXER FOR A TURBOFAN ENGINE 有权
标题翻译：用于涡轮发动机的BLOOM混合器
公开(公告)号：US20120067025A1
公开(公告)日：2012-03-22
申请号：US13231409
申请日：2011-09-13
申请人： Robert THIES
发明人： Robert THIES
IPC分类号： F02K3/075
CPC分类号： F02K1/386 , F02K1/383 , F02K1/48 , F02K3/075 , F05D2240/126
摘要： An adjustable bloom mixer for a turbofan engine for setting a mixing ratio, adapted to the respective flight condition, between cold airflow in the bypass duct and hot airflow in the core flow duct includes an air-guiding element (13) arranged upstream of a thin-walled, corrugated part (6b) of the bloom mixer (6) for branching off a cold partial airflow and/or a hot partial airflow from the bypass duct and from the core flow duct of the engine. An air control device (14) is assigned to the air-guiding element (13) for leading the branched-off cold airflow or hot airflow along the inner surface and/or the outer surface of the bloom mixer (6) in order to deflect its corrugated part (6b) radially inwards or outwards on the basis of a temperature difference between an inner and an outer surface effected by the hot and/or cold partial airflow.
摘要翻译：一种用于涡轮风扇发动机的可调节的起重混合器，用于设置适于各个飞行状态的混合比，在旁路管道中的冷气流与芯流道中的热气流之间包括空气引导元件（13），其布置在薄的用于将冷部分空气流和/或来自旁路管道和来自发动机的核心流动管道的热部分气流分流出来的，用于分配出来的混合器（6）的壁的波纹部分（6b）。空气控制装置（14）被分配到空气引导元件（13），用于引导分流冷气流或沿着盛油混合器（6）的内表面和/或外表面的热气流，以便偏转其波纹部分（6b）基于由热和/或冷部分气流影响的内表面和外表面之间的温度差径向向内或向外径向。

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