公开(公告)号：US5000399A

公开(公告)日：1991-03-19

申请号：US483693

申请日：1990-02-23

申请人： Jack L. Readnour ,  Jack D. Wright

发明人： Jack L. Readnour ,  Jack D. Wright

IPC分类号： B64D33/02 ,  F02C7/042

CPC分类号： B64D33/02 ,  F02C7/042 ,  Y02T50/671

摘要： An annular nacelle for a turbine engine of an aircraft has a variable contour annular air inlet. The variable contour annular inlet includes annular outer and inner surface-defining radially-spaced structures on the forward portion of the nacelle, an annular member disposed between the annular outer and inner structures and coupled to the annular outer structure for sliding movement along the interiors of the annular outer and inner structures, and a plurality of actuating mechanisms coupled between the nacelle body and the annular member. The actuating mechanisms are operable for moving the annular member between forward and rearward positions. At the forward position, the annular member is located between the forward ends of the annular outer and inner structures with the annular outer structure expanded to an enlarged diameter such that the annular member forms therewith an inlet lip having an aerodynamically blunt exterior contour adapted to reduce drag during takeoff and landing operation of the aircraft. At the rearward position, the annular member is spaced rearwardly from the forward ends of the annular outer and inner structures with the annular outer structure contracted to a reduced diameter permitting the annular outer and inner structures at the forward ends thereof to form an inlet lip having an aerodynamically sharp exterior contour adapted to reduce drag during cruise operation of the aircraft.

摘要翻译： 用于飞行器的涡轮发动机的环形机舱具有可变轮廓的环形空气入口。 可变轮廓环形入口包括在机舱的前部上的环形外表面和内表面限定的径向间隔的结构，环形构件，设置在环形外结构和内结构之间并且联接到环形外结构，以沿着内部结构的内部滑动 环形外部和内部结构以及联接在机舱主体和环形构件之间的多个致动机构。 致动机构可操作以使环形构件在前后位置之间移动。 在向前位置处，环形构件位于环形外部结构和内部结构的前端之间，其中环形外部结构膨胀到扩大的直径，使得环形构件与其形成具有适于减少的空气动力学钝的外部轮廓的入口唇缘 在飞机起飞和着陆操作期间拖动。 在后部位置，环形构件与环形外部结构和内部结构的前端向后间隔开，其中环形外部结构收缩到减小的直径，允许其前端处的环形外部和内部结构形成入口唇缘， 适合在航空器巡航操作期间减少阻力的空气动力学锐利的外部轮廓。

公开(公告)号：US4335573A

公开(公告)日：1982-06-22

申请号：US78333

申请日：1970-09-02

申请人： Jack D. Wright

发明人： Jack D. Wright

IPC分类号： F02K1/38 ,  F02K1/82 ,  F02K3/10 ,  F02K3/04

CPC分类号： F02K1/386 ,  F02K1/825

摘要： An afterburning turbofan engine includes amixer for mixing the engine generated hot gas and fan streams prior to discharge through the engine nozzle. The mixer includes a fixed upstream portion and a movable downstream portion which may be indexed to selectively interchange flow communication between the chutes of the two portions to effect a temperature reduction in the downstream mixer portion and, hence, a reduction in infrared radiation.

摘要翻译： 后燃烧涡轮风扇发动机包括用于在发动机喷嘴排出之前混合发动机产生的热气体和风扇流的混合器。 混合器包括固定的上游部分和可移动的下游部分，可移动的下游部分可以被转位以选择性地交换两部分的滑槽之间的流动连通，以在下游混合器部分中实现温度降低，并因此降低红外辐射。

公开(公告)号：USD286880S

公开(公告)日：1986-11-25

申请号：US586372

申请日：1984-03-05

申请人： Leroy H. Smith, Jr. ,  Ambrose A. Hauser ,  William C. Ruehr ,  Alan R. Stuart ,  Jack D. Wright

设计人： Leroy H. Smith, Jr. ,  Ambrose A. Hauser ,  William C. Ruehr ,  Alan R. Stuart ,  Jack D. Wright

公开(公告)号：US5313788A

公开(公告)日：1994-05-24

申请号：US38565

申请日：1993-03-26

申请人： Jack D. Wright ,  Joe E. Ellis

发明人： Jack D. Wright ,  Joe E. Ellis

IPC分类号： F02K1/72 ,  F02K3/02

CPC分类号： F02K1/72

摘要： A thrust reverser for a long duct mixed flow fan jet engine having a nacelle formed by a fixed forward structure surrounding the fan, a rear fixed structure and a translatable inner and outer cowl therebetween, the nacelle surrounds the engine and forms a long by-pass duct therewith, a common actuator fixed to the translatable cowls to simultaneously displace them over the rear structure, blocker doors coupled to the inner translating cowls for deployment during thrust reversal into the by-pass duct into a blocking position to divert the airflow through the cascades placed into an opening uncovered when the translatable cowls are axially displaced.

摘要翻译： 一种用于长管道混合风扇喷气发动机的推力反向器，其具有由围绕风扇的固定的正向结构形成的机舱，后固定结构和可平移的内外罩之间，所述机舱围绕发动机并形成长的旁路 通道，固定在可平移的整流罩上以同时将它们移动到后部结构上的共同致动器，联接到内翻转罩的阻挡门，用于在推力反向进入旁通管道期间展开以阻挡气流通过级联 当可移动的整流罩轴向移位时，它被放置在未被覆盖的开口中。

公开(公告)号：US4275560A

公开(公告)日：1981-06-30

申请号：US973765

申请日：1978-12-27

申请人： Jack D. Wright ,  Barton H. Snow

发明人： Jack D. Wright ,  Barton H. Snow

IPC分类号： F02C9/00 ,  F02C9/22 ,  F02K3/075 ,  F02K3/02 ,  F01B25/02

CPC分类号： F02K3/075 ,  Y02T50/671

摘要： The angle of the variable blocker door vanes in the bypass duct of a turbofan engine is varied in response to the angle of the variable compressor vanes of the engine. A cam and linkage assembly interconnect the blocker doors with the actuation system of the variable stator vanes such that as the angle of the stator vanes is modulated through a first predetermined range, the angle of the blocker doors is modulated through a second predetermined range.

摘要翻译： 涡轮风扇发动机的旁通管道中的可变阻塞门叶片的角度响应于发动机的可变压缩机叶片的角度而变化。 凸轮和连杆组件将阻挡门与可变定子叶片的致动系统互连，使得当定子叶片的角度经过第一预定范围被调制时，阻挡门的角度被调制到第二预定范围。