公开(公告)号：US09163584B2

公开(公告)日：2015-10-20

申请号：US14486521

申请日：2014-09-15

申请人： Foret Plasma Labs, LLC

发明人： Todd Foret

IPC分类号： B64G1/40 ,  F02K3/12 ,  F02C3/14 ,  F02C7/266 ,  H05H1/24 ,  H05H1/32 ,  F02K9/42 ,  F01D13/00 ,  F23R3/00 ,  F23R3/58 ,  G21D5/02

CPC分类号： F02K3/12 ,  B64G1/405 ,  B64G1/406 ,  F01D13/00 ,  F02C3/14 ,  F02C7/266 ,  F02K9/425 ,  F23R3/007 ,  F23R3/58 ,  F23R2900/00002 ,  F23R2900/00009 ,  G21D5/02 ,  H05H1/24 ,  H05H1/32 ,  H05H1/48 ,  H05H2001/4695 ,  Y02E50/12 ,  Y02T50/678

摘要： The present invention provides a plasma arc torch that can be used for lean combustion. The plasma arc torch includes a cylindrical vessel, an electrode housing connected to the first end of the cylindrical vessel such that a first electrode is (a) aligned with a longitudinal axis of the cylindrical vessel, and (b) extends into the cylindrical vessel, a linear actuator connected to the first electrode to adjust a position of the first electrode, a hollow electrode nozzle connected to the second end of the cylindrical vessel such that the center line of the hollow electrode nozzle is aligned with the longitudinal axis of the cylindrical vessel, and wherein the tangential inlet and the tangential outlet create a vortex within the cylindrical vessel, and the first electrode and the hollow electrode nozzle create a plasma that discharges through the hollow electrode nozzle.

摘要翻译： 本发明提供了可用于稀薄燃烧的等离子弧焊炬。 等离子弧焊炬包括圆柱形容器，连接到圆柱形容器的第一端的电极壳体，使得第一电极（a）与圆柱形容器的纵向轴线对准，并且（b）延伸到圆柱形容器中， 连接到第一电极以调节第一电极的位置的线性致动器，连接到圆柱形容器的第二端的中空电极喷嘴，使得中空电极喷嘴的中心线与圆柱形容器的纵向轴线对准 并且其中所述切向入口和所述切向出口在所述圆柱形容器内产生涡流，并且所述第一电极和所述中空电极喷嘴产生通过所述中空电极喷嘴排出的等离子体。

公开(公告)号：US06926232B2

公开(公告)日：2005-08-09

申请号：US10167419

申请日：2002-06-13

申请人： Michel Franchet ,  Yann Laugier ,  Jean Loisy

发明人： Michel Franchet ,  Yann Laugier ,  Jean Loisy

IPC分类号： F02C7/36 ,  F02C3/14 ,  F02C9/18 ,  F02K3/02 ,  F02K3/075 ,  F02K3/12 ,  B64D27/00

CPC分类号： F02K3/025 ,  F02K3/075 ,  F02K3/12 ,  Y02T50/671

摘要： A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having at least one compressor and capable of generating thrust for supersonic flight speeds, and at least one auxiliary propulsion assembly separate from said engine, and capable of generating additional thrust for takeoff, landing, and subsonic cruising speeds, at least one pipe connecting the engine to the auxiliary propulsion assembly to convey thereto compressed air produced by the compressor so as to enable the auxiliary propulsion assembly to generate additional thrust for takeoff, landing, and subsonic cruising flight, there being at least one valve enabling the pipe to be closed off for supersonic cruising flight.

摘要翻译： 一种用于超音速飞机的可变循环推进系统，该系统包括至少一个具有至少一个压缩机并能够产生用于超音速飞行速度的推力的发动机，以及与所述发动机分离的至少一个辅助推进组件，并且能够产生额外的推力 用于起飞，着陆和亚音速巡航速度，至少一个管道将发动机连接到辅助推进组件以将由压缩机产生的压缩空气输送到辅助推进组件，以使辅助推进组件产生用于起飞，着陆和亚音速的附加推力 巡航飞行，至少有一个阀门使管道能够被关闭用于超音速巡航飞行。

公开(公告)号：US4519208A

公开(公告)日：1985-05-28

申请号：US420914

申请日：1982-09-21

申请人： Jean M. Loisy ,  Claude C. F. Menioux

发明人： Jean M. Loisy ,  Claude C. F. Menioux

IPC分类号： F02K3/075 ,  F02K3/105 ,  F02K3/12 ,  F02K3/06

CPC分类号： F02K3/12 ,  F02K3/075 ,  F02K3/105 ,  Y02T50/671

摘要： The invention relates to a propulsion engine, particularly for supersonic aircraft. An internal propulsion system comprises an envelope displaying a tapered center portion, around which is coaxially mounted an external propulsion system which lacks a separate compressor. According to the invention, mechanisms are provided to divert toward the combustion chamber of the external propulsion system an adjustable fraction of the compressed air arriving from the last compressor stage of the internal propulsion system. A blower which is driven by the external turbine exhausts in parallel with the latter into an annular conduit which emerges between the internal nozzle and external nozzle and an exhaust nozzle, all of these nozzles being of variable geometry. The purpose of the invention is to improve variable cycle propulsion engines for second-generation supersonic aircraft.

摘要翻译： 本发明涉及一种推进发动机，特别是用于超音速飞行器。 内部推进系统包括显示锥形中心部分的外壳，其同轴地安装有缺少单独的压缩机的外部推进系统。 根据本发明，提供了一种机构，用于向外部推进系统的燃烧室转移从内部推进系统的最后一个压缩机级到达的压缩空气的可调部分。 由外部涡轮机驱动的鼓风机与后者平行排放到环形管道中，该管道出现在内部喷嘴和外部喷嘴之间以及排气喷嘴之间，所有这些喷嘴都具有可变的几何形状。 本发明的目的是改进用于第二代超音速飞机的可变循环推进发动机。

公开(公告)号：US4259838A

公开(公告)日：1981-04-07

申请号：US52167

申请日：1979-06-26

申请人： James H. McCollum, Jr. ,  Leo P. Kammerer

发明人： James H. McCollum, Jr. ,  Leo P. Kammerer

IPC分类号： F02C9/42 ,  F02K3/12

CPC分类号： F02C9/42

摘要： A throttle servo for each engine of a multiengine aircraft and servo tracking means for detecting and compensating for servo drift during autothrottle mode of operation.

摘要翻译： 用于多引擎飞机的每个发动机的油门伺服器和用于在自动油门操作模式期间检测和补偿伺服漂移的伺服跟踪装置。

公开(公告)号：US4248041A

公开(公告)日：1981-02-03

申请号：US957033

申请日：1978-10-27

申请人： Geoffrey L. Wilde ,  Maurice I. Taylor ,  Geoffrey P. Medland

发明人： Geoffrey L. Wilde ,  Maurice I. Taylor ,  Geoffrey P. Medland

IPC分类号： B64C29/00 ,  F02K3/12 ,  F02K1/10 ,  F02K3/06

CPC分类号： B64C29/0066 ,  F02K3/12

摘要： A V.S.T.O.L. gas turbine power plant includes a main gas turbine engine having an exhaust gas propulsion nozzle and a fan arranged within a fan duct, which duct terminates in two nozzles such that a portion of the fan air may be directed vertically downwards or horizontally, the remaining portion of the fan air acts as a working fluid in one or more further auxiliary gas turbine engines each engine including a vectorable exhaust nozzle.

摘要翻译： V.S.T.O.L. 燃气轮机发电厂包括具有排气推进喷嘴和布置在风扇管道内的风扇的主燃气涡轮发动机，该管道终止于两个喷嘴，使得风扇空气的一部分可以垂直向下或向下定向，其余部分 风扇空气在一个或多个另外的辅助燃气涡轮发动机中用作工作流体，每个发动机包括可引导的排气喷嘴。

公开(公告)号：US3972349A

公开(公告)日：1976-08-03

申请号：US481439

申请日：1974-06-20

申请人： Julius W. Tumavicus

发明人： Julius W. Tumavicus

IPC分类号： F02K3/075 ,  F16K11/00 ,  F02K3/12

CPC分类号： F02K3/075 ,  Y02T50/671 ,  Y10T137/87764 ,  Y10T137/87772

摘要： An inverter valve arrangement which comprises a fixed forward duct system having concentric annular passages at its inlet and a fixed after duct system having concentric annular passages at its outlet and each fixed system having selectively shaped adjacent portions which are circumferentially displaced and joined by a plurality of flapper valves. The flapper valves may be actuated so that either series or parallel flow will occur between the concentric annular passages of the systems.

摘要翻译： 一种逆变器阀装置，其包括在其入口处具有同心环形通道的固定前进管道系统和固定的后管道系统，其出口处具有同心的环形通道，并且每个固定系统具有选择性地成形的相邻部分，其周向位移并通过多个 挡板阀。 挡板阀可以被致动，使得在系统的同心环形通道之间将发生串联或平行流动。

公开(公告)号：US3841091A

公开(公告)日：1974-10-15

申请号：US36248573

申请日：1973-05-21

申请人： GEN ELECTRIC

发明人： SARGISSON D ,  RUNDELL D

IPC分类号： F02C3/13 ,  F02C6/00 ,  F02K1/08 ,  F02K3/075 ,  F02K3/12

CPC分类号： F02C6/00 ,  F02C3/13 ,  F02K1/08 ,  F02K3/075 ,  F02K3/12 ,  F05D2250/311

摘要： A multi-mission tandem propulsion system is provided for an aircraft which must operate efficiently at both supersonic and subsonic speeds while generating low noise levels during takeoff, accelerated climb to altitude, approach to landing, and landing. The propulsion system includes a forward turbofan engine coaxially spaced apart from an aft turbojet engine wherein both engines may be selectively controlled to provide overall maximum efficiency during all modes of operation.

摘要翻译： 为飞机提供了一个多任务串联推进系统，该飞机必须在超音速和亚音速下均有效地运行，同时在起飞期间产生低噪音水平，加速爬升到高度，接近着陆和降落。 推进系统包括与后涡轮喷气发动机同轴间隔开的前进涡轮风扇发动机，其中可以选择性地控制两个发动机，以在所有操作模式期间提供总体最大效率。

公开(公告)号：US3656302A

公开(公告)日：1972-04-18

申请号：US3656302D

申请日：1970-08-11

申请人： TECHNOLOGY UK

发明人： TOWNEND LIONEL HENRY

IPC分类号： F02K1/52 ,  F02K3/10 ,  F02K1/06 ,  F02K3/12

CPC分类号： F02K1/52

摘要： A multiple jet, aircraft engine exhaust installation comprising at least two engine exhaust nozzles, aircraft structure joining said exhaust nozzles, means for supplying fuel to be burnt at a region immediately aft of said joining aircraft structure, outlet orifices terminating said exhaust nozzles at exit planes, said exit planes being convergent in the upstream sense, ducts defining an outlet passage for exhaust gases in said nozzles and extending from duct throats within said nozzles to said outlet orifices and wherein said ducts are shaped in accordance with the supersonic Prandtl-Meyer flow theory of supersonic expansion.

摘要翻译： 一种多喷射飞机发动机排气装置，包括至少两个发动机排气喷嘴，连接所述排气喷嘴的飞行器结构，用于供应在所述连接飞行器结构的紧后面的区域燃烧的燃料的装置，在出口平面处终止所述排气喷嘴的出口孔 所述出口平面在上游方向收敛，管道限定出在所述喷嘴中的废气的出口通道并从所述喷嘴内的管道喉部延伸到所述出口孔，并且其中所述管道根据超音速普朗特迈尔流动理论 的超音速膨胀。

公开(公告)号：US3489377A

公开(公告)日：1970-01-13

申请号：US3489377D

申请日：1968-12-16

申请人： ROLLS ROYCE

发明人： PEARSON KENNETH ARTHUR ,  WRIGHT GEOFFREY HARRY

IPC分类号： F02C7/045 ,  F02C7/32 ,  F02K1/82 ,  F02K3/12 ,  B64D41/00 ,  B64D33/06

CPC分类号： F02C7/045 ,  B64D41/00 ,  B64D2033/0213 ,  B64D2041/002 ,  F02C7/32 ,  F02K1/827 ,  F02K3/12 ,  Y10T137/0536

摘要： 1,212,875. Aircraft power plant. ROLLSROYCE Ltd. 19 Dec., 1968 [21 Dec., 1967], No. 58059/67. Heading B7G. [Also in Division F1] The invention relates to an aircraft which has at least one main forward propulsion engine and an auxiliary gas turbine engine, the auxiliary engine being capable of operating in two modes, the first mode being one in which the engine produces forward thrust and the second mode being one in which the engine drives equipment to provide aircraft services independently of the main engine. A propulsion nozzle is provided for flow of exhaust gases from the auxiliary engine when operating to produce forward thrust. A shaft is provided for driving aircraft equipment from the auxiliary engine. Means are provided for silencing the intake of the auxiliary engine when it is operating in the second mode, and further means are provided for silencing the exhaust gas discharge from the auxiliary engine when it is operating in the second mode. The aircraft shown has two forward propulsion engines 2 and a single auxiliary gas turbine engine 3 which is mounted in the rear part of the fuselage. The auxiliary engine has two air intake ducts 6 and a propulsion nozzle 10 also an exhaust gas outlet 9 located at the top of the fuselage. A pivotally mounted flap member 12 is provided which may be positioned to block the outlet 9 when the engine is producing forward thrust or to block the propulsion nozzle 10 when the engine is driving the aircraft auxiliaries. A series of splitters 11 formed of sound absorbing material are located in the exhaust gas outlet. A series of splitters 16 are disposed in each of the intake ducts 6, the splitters being made of sound absorbing material. The shaft of the auxiliary engine is extended by means of a coupling 20 and shaft 21 to drive a gear-box 24 through a clutch 23. Aircraft auxiliaries such as an air compressor 27 and generator 25 are driven from the gear-box. The splitters in the air intakes may be retracta,ble as indicated in Fig. 4. The splitters are shown in the operative position at the lower part of the Figure and in the retracted, inoperative position in full lines at the upper part of the Figure; the splitters may be moved to close off the intake opening as shown in chain-dotted lines at the upper part of the Figure. The splitters may be connected together by a lazytongs linkage. Each intako duct such as 6 in Fig. 1 may have two inlet openings, one opening being unobstructed and being used when the auxiliary engine is pro u ing forward thrust, and the other opening being provided with silencing splitters and being lined with sound absorbing material, this opening being used when the auxiliary engine is driving aircraft auxiliaries.

公开(公告)号：US3440821A

公开(公告)日：1969-04-29

申请号：US3440821D

申请日：1967-11-13

申请人： BOLKOW GMBH

发明人： WALTZ OTTO

IPC分类号： F02K9/48 ,  F02K3/12 ,  F02K9/02

CPC分类号： F02K9/48