公开(公告)号：US3579993A

公开(公告)日：1971-05-25

申请号：US3579993D

申请日：1969-08-04

申请人： ROHR CORP

发明人： TANNER CAROLE S ,  TONTINI REMO

IPC分类号： F02K1/36 ,  F02K1/40 ,  F02K3/04 ,  B64D33/06

CPC分类号： F02K1/40 ,  F02K1/36 ,  F05D2260/962 ,  Y02T50/671

摘要： System includes a nozzle connected to turbine exhaust outlet to confine and direct gas stream. Nozzle is corrugated to form peripherally spaced radially extending lobes to divide gas into small jet streams. Conduit surrounds exhaust outlet and discharges to exterior of nozzle, and fan air flows through passages between lobes to meet gas streams at exit margin of nozzle. Shroud or ejector sleeve defines and surrounds a mixing zone aft of the exit margin. Leading edge of shroud is spaced aft of fan air conduit to provide annular flow path for entry of ambient air to surround and mix with fan air and gas. Shroud is retractable to surround nozzle in spaced relation and prevent dispersion of fan air before mixing in normal cruising flight.

公开(公告)号：US3568793A

公开(公告)日：1971-03-09

申请号：US3568793D

申请日：1969-09-25

申请人： ROHR CORP

发明人： MILLMAN VICTOR ,  TONTINI REMO

IPC分类号： F02K1/44 ,  F01N1/14 ,  B64D33/06 ,  F01N1/16

CPC分类号： F02K1/44

摘要： Support means carried by engine housing has pivotal mounting means at aft end. Support means is axially slidable between forward stowed position and aft deployed position. In latter, pivotal mounting means is adjacent to nozzle exit. Noise shield is swingably mounted on mounting means to swing vertically on lateral axis. Shield is elongate and preferably trough shaped to surround jet stream and reflect noise upward. Optimum results require holding shield at suitable angle to intercept expansion boundary of jet stream. Upper or inner surface of shield is formed with leading edge lip contiguous to jet stream at nozzle exit, followed by depressed forward portion, raised intermediate portion and tapered aft portion. Leading edge lip produces Coanda-type attachment to jet stream, depressed portion produces reduced static pressure to urge shield into interception position, and tapered aft portion produces increasing pressure gradient to oppose effect of forward portion and trim shield to position for optimum thrust and noise attenuation. When support means is stowed, shield is carried forward to stow in streamlined relation to engine housing.

公开(公告)号：US3650472A

公开(公告)日：1972-03-21

申请号：US3650472D

申请日：1970-10-16

申请人： ROHR CORP

发明人： TONTINI REMO ,  JOHNSEN RAYMOND K

IPC分类号： F02K1/34 ,  F02K1/36 ,  F02K1/38 ,  B64D33/06

CPC分类号： F02K1/36 ,  F02K1/34 ,  F02K1/386 ,  Y02T50/671

摘要： Engine of either turbo fan or turbojet type is provided with multiple lobed exhaust nozzle. An ejector barrel defining a mixing zone is adapted to be connected at its leading edge to the lobe tips adjacent to the nozzle exit plane to receive engine gases and free stream air. A plenum chamber in the forward portion of the barrel has inlet ports in flow communication with tip portions of lobes, and guide vanes extend forward into lobes to split the mixed engine gases and guide outer streams into plenum chamber inlet ports while inner streams flow directly to mixing zone. An annular control nozzle at aft end of plenum chamber discharges high pressure gases into intermediate section of mixing zone to form a gaseous ring surrounding the other gases. The high velocity flow at inner wall increases total flow and makes velocity profile more uniform, and further mixing with adjacent gases reduced sound level. Design of control nozzle determines profile of gaseous ring which becomes virtual aerodynamic profile of aft portion of ejector barrel, which may be convergent-divergent nozzle shape for optimum cruise conditions of a high subsonic aircraft. Nozzle may also be adjustable to produce varying profiles for varying flight regimes. Basic design makes it possible to incorporate thrust reverser in aft portion of ejector barrel.

摘要翻译： 涡轮风扇或涡轮喷气式发动机配有多个叶片式排气喷嘴。 限定混合区的喷射器筒适于在其前缘连接到与喷嘴出口平面相邻的叶尖，以接收发动机气体和自由流空气。 在筒的前部中的增压室具有与叶片的尖端部分流动连通的入口端口，并且导向叶片向前延伸到叶片中以分裂混合的发动机气体并将外部流引导到增压室入口端口，同时内部流体直接流向 混合区。 增压室后端的环形控制喷嘴将高压气体排放到混合区的中间部分，形成围绕其它气体的气态环。 内壁高速流动增加总流量，使速度分布更加均匀，与邻近气体的进一步混合降低了声级。 控制喷嘴的设计确定气态环的轮廓，其成为喷射器筒的后部的虚拟空气动力学轮廓，其可以是会聚发散的喷嘴形状，用于高亚音速飞机的最佳巡航条件。 喷嘴也可以是可调节的，以产生用于不同飞行状态的不同轮廓。 基本设计使得可以将推力反向器并入推出筒的后部。

公开(公告)号：US3591087A

公开(公告)日：1971-07-06

申请号：US3591087D

申请日：1969-05-08

申请人： ROHR CORP

发明人： TONTINI REMO

IPC分类号： F02K1/36 ,  B64C15/10

CPC分类号： F02K1/36

摘要： The jetstream flowing through a tubular thrust ejector is prevented from detaching from the inner surface thereof by admitting a portion of the boundary layer of said jetstream into holes which terminate within an area encircling the aft portion of said inner surface and which communicate with the forward portion of the ejector throat.

公开(公告)号：US3590944A

公开(公告)日：1971-07-06

申请号：US3590944D

申请日：1969-04-17

申请人： ROHR CORP

发明人： MILLMAN VICTOR ,  TONTINI REMO ,  KAMPS EDWIN C

IPC分类号： B64C9/38 ,  B64D33/04 ,  B64D33/06

CPC分类号： B64D33/06

摘要： A panel of substantially hemicylindrical form is mounted on the engine nacelle of a jet-propelled aircraft with the longitudinal axis of the panel extending axially of the nacelle. The panel is movable axially of the nacelle between a retracted position wherein it is alongside the latter and a deployed position wherein it is disposed downstream from the nacelle and tilted upwardly at an angle relative to the longitudinal axis of the thrust nozzle of the engine contained in the nacelle so as to intercept the expansion boundary of the jet stream issuing from said nozzle several nozzle diameters downstream of the nozzle. Means are provided for moving the panel between its retracted and deployed positions.

公开(公告)号：US3575260A

公开(公告)日：1971-04-20

申请号：US3575260D

申请日：1969-05-15

申请人： ROHR CORP

发明人： URGUHART GEORGE R ,  TONTINI REMO

IPC分类号： F02K1/36 ,  F02K1/44 ,  F01N1/14 ,  B64D33/06 ,  F01N1/16

CPC分类号： F02K1/36 ,  F02K1/44

摘要： A tubular ejector is mounted on the nacelle of a jet-propelled aircraft so that it can be stowed alongside the nacelle or positioned downstream therefrom. A pair of hemicylindrical panels are mounted on the lower portion of the outer side of the ejector for movement between a stowed position alongside the ejector and a deployed position wherein one of the panels projects from the aft end of the ejector and the other panel projects from the aft end of said one panel. The jet stream flowing through the ejector is prevented from detaching from the inner surface thereof by admitting a portion of the boundary layer of said jet stream into holes which terminate within an area encircling the aft portion of said inner surface and which communicate with the forward portion of the ejector throat.

公开(公告)号：US3565208A

公开(公告)日：1971-02-23

申请号：US3565208D

申请日：1970-02-02

申请人： ROHR CORP

发明人： MILLMAN VICTOR ,  TONTINI REMO

IPC分类号： F02K1/44 ,  F01N1/00 ,  B64D33/06

CPC分类号： F02K1/44

摘要： Support means carried by an aircraft jet engine housing has pivots at its aft end and is slidable axially of the housing between forward stowed position and aft deployed position, said pivots being located adjacent exit of engine nozzle in latter position. Elongate shield is mounted on the pivots to swing vertically about an axis transverse to longitudinal axis of housing, and is preferably trough-shaped to surround jetstream discharged from the nozzle and reflect noise upward. Aft end of shield is supported or forced up in flight by aerodynamic reacting vanes mounted on inner side of said aft end. When support means is stowed, shield is carried forward to stow in streamlined relation to housing.