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41. 发明授权

US2696079A Dual jet aircraft power plant 失效
标题翻译：双喷气机发电厂
公开(公告)号：US2696079A
公开(公告)日：1954-12-07
申请号：US15643150
申请日：1950-04-17
申请人： KAPPUS PETER G
发明人： KAPPUS PETER G
IPC分类号： F02K1/58 , F02K1/64 , F02K3/04 , F02K3/11 , F02K7/16
CPC分类号： F02K3/11 , F02K1/58 , F02K1/64 , F02K3/04 , F02K7/16

42. 发明授权

US12000358B1 Gas turbine engine nozzle loft for thrust reverser 有权
公开(公告)号：US12000358B1
公开(公告)日：2024-06-04
申请号：US18109428
申请日：2023-02-14
申请人： Pratt & Whitney Canada Corp.
发明人： Mark Cunningham , Eray Akcayoz
IPC分类号： F02K1/62 , F02K1/58
CPC分类号： F02K1/62 , F02K1/58 , F05D2220/323
摘要： An engine nacelle assembly includes a nacelle that defines a flow path between an intake end and an exhaust end, and a nozzle that is disposed at the exhaust end of the nacelle about a central axis. The nozzle includes opposing thrust reverser openings and thrust reverser doors. A cross-sectional area transverse to the central axis proximate a forward side of each of the opposing thrust reverser openings is oval shaped with an offset radius within offset arc segments that are aligned with the opposing thrust reverser openings and a first radius outside of the offset arc segment. The first radius is less than the offset radius.

43. 发明申请

US20180230940A1 LOAD DISTRIBUTION PANEL ASSEMBLY, SYSTEM AND METHOD 审中-公开
公开(公告)号：US20180230940A1
公开(公告)日：2018-08-16
申请号：US15387620
申请日：2016-12-21
申请人： The Boeing Company
发明人： Luke D. Torjesen , Robert D. Morrow
IPC分类号： F02K1/72 , F02K1/58 , B64D29/06 , B64D33/04
CPC分类号： F02K1/72 , B64D29/06 , B64D33/04 , F02K1/58 , F02K1/763 , F05D2220/323 , Y02T50/672
摘要： There is provided a load distribution panel assembly for a gas turbine engine. The assembly has a panel structure having at least one circumferential structural panel having a first end, and a second end coupled to a fixed structure of the gas turbine engine. The circumferential structural panel has a first compliant portion extending away from the first end, and has a second stiffened portion angled with respect to and extending radially away from the first compliant portion, and terminating at the second end. The second stiffened portion has a closed stiffened cavity portion integral with a perimeter flange portion. The panel assembly converts fore/aft point load(s) applied to it by load applying apparatus(es), to hoop tension and compression loads, and reacts a load offset in in-plane load(s), to provide uniform load distribution of the fore/aft point load(s) to the fixed structure.

44. 发明授权

US09102395B2 Multifunctional propulsive system for an airplane 有权
标题翻译：飞机多功能推进系统
公开(公告)号：US09102395B2
公开(公告)日：2015-08-11
申请号：US12789761
申请日：2010-05-28
申请人： Olivier Cazals , Jaime Genty De La Sagne
发明人： Olivier Cazals , Jaime Genty De La Sagne
IPC分类号： F02K3/02 , F02K1/00 , F02K1/54 , B64C29/00 , B64C15/02 , B64D35/04 , F02K1/58 , F02K1/60 , F02K1/76 , F02K1/12 , F02K1/70 , F02K1/72
CPC分类号： B64C15/02 , B64D35/04 , F02K1/008 , F02K1/12 , F02K1/1223 , F02K1/58 , F02K1/60 , F02K1/70 , F02K1/72 , F02K1/763 , Y02T50/671
摘要： A propulsive system for aircraft that has a jet engine and a nacelle surrounding the aforementioned jet engine. The nacelle has a front section fixed relative to the jet engine, and a rear extremity behind the front section, and has a rear section with two petals hinged relative to the front section. Each of the two petals in a position called zero-setting forms an extension of the front section of the nacelle in which the inside and outside surfaces of the petals and, respectively, determine the aerodynamic forms of the rear section, which are in geometric continuity with the inside and outside surfaces and, respectively, that determine the aerodynamic forms of the front section. The petals can be set individually at a positive or negative setting angle to put into play the reverser, APU, air brake, vectorial, and taxiing modes of the propulsive system.
摘要翻译：用于具有喷气发动机和围绕上述喷气发动机的机舱的飞行器的推进系统。机舱具有相对于喷气发动机固定的前部分，并且在前部后方具有后端，并且具有后部，其具有相对于前部铰接的两个瓣。位于称为零位置的两个花瓣中的每一个形成机舱的前部的延伸部，其中花瓣的内侧和外侧表面分别确定后部的空气动力学形状，其具有几何连续性内表面和外表面分别确定前部的空气动力学形式。花瓣可以以正或负设置角度单独设置，以投入推进系统的反向器，APU，空气制动，矢量和滑行模式。

45. 发明授权

US4252286A Simplified core flow thrust control device 失效
标题翻译：简化核心流量推力控制装置
公开(公告)号：US4252286A
公开(公告)日：1981-02-24
申请号：US030266
申请日：1979-04-16
申请人： James R. Moorehead
发明人： James R. Moorehead
IPC分类号： B64D33/04 , F02K1/58 , B64C15/00 , F02K1/54
CPC分类号： B64D33/04 , F02K1/58 , Y02T50/671
摘要： There is disclosed a simplified, lightweight, easily stowed thrust control device for the hot core exhaust flow of a jet engine. The device is mounted in the engine strut fairing, downstream of the nozzle exit plane to reduce exposure to the high exhaust temperatures. In a blocking position, the mounting hardware, actuator and actuator linkage is located so as to be cooled by both free stream and fan air, providing a longer operating life, less maintenance and more reliable operation. Simplified construction and mounting arrangement permit the device to be readily retrofitted on existing installations.
摘要翻译：公开了一种用于喷气发动机的热芯排气流的简化的，轻便的，容易收起的推力控制装置。该装置安装在发动机支柱整流罩中，在喷嘴出口平面的下游，以减少暴露于高排气温度。在阻塞位置，安装硬件，执行器和执行器联动装置被定位以便通过自由流和风扇空气来冷却，提供更长的使用寿命，更少的维护和更可靠的操作。简化的结构和安装布置使得设备可以在现有的设备上进行改装。

46. 发明授权

US3774868A Integrated nozzle 失效
标题翻译：集成喷嘴
公开(公告)号：US3774868A
公开(公告)日：1973-11-27
申请号：US3774868D
申请日：1972-12-11
申请人： GOETZ G
发明人： GOETZ G
IPC分类号： F02K1/08 , F02K1/58 , B64D33/04 , B63H11/10 , B64C15/00
CPC分类号： F02K1/58 , F02K1/08
摘要： An aircraft engine exhaust nozzle system having thrust vectoring capability for use in flight path management, for in-flight thrust reversal or modulation, or for thrust reversal during landing; and which includes a variable area nozzle for improved propulsion efficiency. The preferred embodiment utilizes an exhaust passageway having a rectangular nozzle exit area for minimum base area, boattail, and interference drag. An aerodynamically shaped plug is centrally located in the path of the exhaust gases. The portion of the plug extending aft of the nozzle exit plane is used as a thrust vector control means and comprises a pair of oppositely facing surfaces which can be displaced for changing the flow pattern of the exhaust gases, thereby generating a thrust vector for use as a primary flight control in rotating the aircraft about one of its major axes. The oppositely facing surfaces can also be positioned for forward thrust modulation or for full reversal of the thrust vector. A portion of the plug extending forward of the exit plane provides for variable throat area control by displacement of plug surface panels to obtain a desired nozzle throat area and, independently, a passageway shape and exit area for improved propulsion efficiency.
摘要翻译：飞机发动机排气喷嘴系统，具有推进矢量化功能，用于飞行路径管理，用于飞行中推力反转或调制，或用于降落期间的推力反转; 并且其包括用于改进的推进效率的可变区域喷嘴。优选实施例利用具有矩形喷嘴出口区域的排气通道，用于最小基座面积，火炬和干涉阻力。空气动力学形状的塞子位于排气路径的中心。在喷嘴出口平面后面延伸的插头的部分用作推力矢量控制装置，并且包括一对相对的表面，该表面可以被移位以改变废气的流动模式，由此产生用作主要飞行控制器使飞机绕其主轴之一旋转。相对的表面也可以被定位用于正向推力调制或用于推力矢量的完全反转。从出口平面向前延伸的塞子的一部分通过插塞表面板的位移来提供可变的喉部区域控制，以获得期望的喷嘴喉部区域，并且独立地通过通道形状和出口区域来改善推进效率。

47. 发明授权

US3330505A Thrust reversal and aerodynamic brake for aircraft 失效
标题翻译：飞机推力反转和气动制动
公开(公告)号：US3330505A
公开(公告)日：1967-07-11
申请号：US45662665
申请日：1965-05-18
申请人： BOLKOW GMBH
发明人： FRANZ SEDLMAIER
IPC分类号： F02K1/58
CPC分类号： F02K1/58 , Y02T50/671

48. 发明授权

US3292864A Thrust reverser and deflector 失效
标题翻译：推力反向器和导流器
公开(公告)号：US3292864A
公开(公告)日：1966-12-20
申请号：US42679465
申请日：1965-01-21
申请人： GEN ELECTRIC
发明人： PIERPOINT EDKINS DENIS
IPC分类号： B64C15/02 , F02K1/58
CPC分类号： B64C15/02 , F02K1/58

49. 发明授权

US3289945A Thrust reverser for plug nozzle 失效
标题翻译：用于插头喷嘴的推力反向器
公开(公告)号：US3289945A
公开(公告)日：1966-12-06
申请号：US34448264
申请日：1964-02-12
申请人： UNITED AIRCRAFT CORP
发明人： NOREN HILMER K
IPC分类号： F02K1/58
CPC分类号： F02K1/58

50. 发明授权

US2838909A Means for the deflection of fluid jets 失效
标题翻译：流体射流偏转的手段
公开(公告)号：US2838909A
公开(公告)日：1958-06-17
申请号：US36632153
申请日：1953-07-06
申请人： SNECMA
发明人： MEULIEN HENRI L P
IPC分类号： F02K1/32 , F02K1/58
CPC分类号： F02K1/32 , F02K1/58

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