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公开(公告)号：US4183478A
公开(公告)日：1980-01-15
申请号：US854554
申请日：1977-11-25
Applicant: Peter K. C. Rudolph
Inventor： Peter K. C. Rudolph
CPC classification number: F02K1/60 , Y02T50/671
Abstract: A cascade/clamshell thrust reverser combination for jet engines wherein the clamshell door in the full-forward thrust mode position, covers a cascade arrangement of vane members provided in the annular engine casing. For obtaining the thrust reverser mode, a track and pivot mechanism is employed. Initially, the door moves backwards on the track while simultaneously slightly rotating so that the total movement of the door follows a predetermined arc. During this initial movement the first portion of the vanes are gradually exposed. Upon continuation towards the full reverser mode, the door will move into a rotating movement thereby fully exposing all vanes and closing the forward thrust nozzle opening. The successive combined track/pivot movement to a pivot rotating movement allows for the maneuvering of a maximum large structural sized clamshell door within the multiple contoured confines of the exit casing, thereby providing the most optimum thrust reverser effect. The invention further resides in tailoring or varying the discharge angles of the vane members of the cascade from front to rear to maintain the effective discharge area for the engine essentially constant during inflight partial deployment of the clamshell door.
Abstract translation: 用于喷气发动机的级联/蛤壳推力反向器组合，其中襟翼门处于全向推力模式位置，覆盖设置在环形发动机壳体中的叶片构件的级联布置。 为了获得推力反向器模式，采用轨道和枢转机构。 最初，门在轨道上向后移动同时轻微旋转，使得门的总运动遵循预定的弧线。 在该初始运动期间，叶片的第一部分逐渐暴露。 当继续朝向全反向模式时，门将移动到旋转运动中，从而完全暴露所有叶片并且关闭向前推力喷嘴开口。 连续组合的轨道/枢转运动到枢转旋转运动允许在出口壳体的多个轮廓范围内操纵最大的大型结构尺寸的翻盖门，从而提供最佳的推力反向器效果。 本发明进一步在于定制或改变级联从前到后的叶片构件的排出角度，以在蛤壳式门的动力部分展开期间维持发动机的有效排放面积基本恒定。
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公开(公告)号：US4099671A
公开(公告)日：1978-07-11
申请号：US722771
申请日：1976-09-13
Applicant: Heinrich Leibach
Inventor： Heinrich Leibach
CPC classification number: F02K1/11
Abstract: Control apparatus for an aircraft is provided which includes a gas-controlled housing disposed downstream of a gas turbine jet propulsion supply system. A propulsion nozzle is provided at the downstream end of a tubular member extending from the control housing in alignment with a longitudinal axis of the engine system. Lateral control outlets extend in opposite lateral directions from the gas-controlled housing. The flow of gases selectively to one or both of the control outlets and to the propulsion nozzle is effected by way of two part-spherical sector control valve members which are mounted for pivotal movement about an axis running perpendicular to the longitudinal axis. The control valve members are configured for selectively blocking the flow of propulsion gases to the propulsion nozzle and the respective lateral control outlets.
Abstract translation: 提供了一种用于飞机的控制装置，其包括设置在燃气轮机喷射推进供应系统下游的气体控制壳体。 推动喷嘴设置在从控制壳体延伸的管状构件的下游端处，与发动机系统的纵向轴线对齐。 横向控制出口从气体控制的壳体向相反的横向方向延伸。 选择性地对一个或两个控制出口和推进喷嘴的气体的流动通过两个部分球形扇形调节阀构件来实现，该两个部分球形扇形调节阀构件安装成围绕垂直于纵向轴线运动的轴线枢转运动。 控制阀构件被构造成用于选择性地阻挡推进气体到推进喷嘴和相应的横向控制出口的流动。
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公开(公告)号：US3797785A
公开(公告)日：1974-03-19
申请号：US3797785D
申请日：1972-08-31
Applicant: ROHR INDUSTRIES INC
Inventor： BAERRESEN R , TIMMS R
Abstract: 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 terminating forward of exit end of nozzle. Aft portion of shroud is a separate sleeve movable axially to define a peripheral outflow gap for fan air. A ring of reverse thrust cascades is located in the gap, and a set of blocker doors are pivoted at their aft ends adjacent to the aft end of the cascade ring. In stowed position they overlie the inner side of the cascade ring and block lateral outflow. In deployed position they converge forward to block rearward flow of air and to divert it out through cascade ring. The sleeve in stowed position overlies the outer side of the cascade ring and prevents inflow, while its trailing edge is in the plane of maximum size of the core to define a convergent nozzle for cruising operation. The sleeve shifts partially aft to a position defining a larger nozzle exit area for takeoff and landing, with the blocker doors stowed and latched. Final deployment of the sleeve releases the latches and positively moves the doors to deployed position. Initial stowing movement of the sleeve positively stows the doors and positively secures the latches.
Abstract translation: 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，以定义用于在喷嘴出口端前方的风扇空气的环形通道。 护罩的后部是可轴向移动的独立套筒，以限定用于风扇空气的外围流出间隙。 一个反向推力级联环位于间隙中，一组阻挡门在靠近级联环的后端的后端枢转。 在收起位置，它们覆盖在级联环的内侧并阻止侧向流出。 在展开位置，它们向前收敛以阻挡空气的向后流动并通过级联环将其分流出来。 收起位置的套筒位于级联环的外侧，防止流入，而其后缘处于芯的最大尺寸的平面中，以限定用于巡航操作的会聚喷嘴。 套筒部分地向后移动到限定用于起飞和着陆的较大喷嘴出口区域的位置，阻挡门被收起并锁定。 套筒的最终部署释放闩锁并将门正向移动到展开位置。 套筒的初始收起运动可以正确地收起门并且牢固地固定闩锁。
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公开(公告)号：US3752401A
公开(公告)日：1973-08-14
申请号：US3752401D
申请日：1968-12-23
Applicant: HONEYWELL INC
Inventor： KIZILOS A
Abstract: A three-dimensional variable deflection thruster for varying the direction of a fluid stream about two mutually orthogonal axes, having no moving parts. A plurality of fluid streams are caused to attach to and flow around a convex three-dimensional surface to impinge on one another and form a resultant fluid stream. The resultant fluid stream departs from the convex surface in a direction which can be controlled by varying the relative strengths and directions of the component fluid streams.
Abstract translation: 三维可变偏转推进器，用于改变围绕两个相互正交的轴线的流体流的方向，没有运动部分。 引起多个流体流附着到一个凸形的三维表面上并流过它们以彼此冲击并形成所得到的流体流。 所得到的流体流在可以通过改变组分流体流的相对强度和方向来控制的方向上离开凸表面。
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公开(公告)号：US3659788A
公开(公告)日：1972-05-02
申请号：US3659788D
申请日：1970-10-14
Applicant: ROLLS ROYCE
Inventor： OLDFIELD HARRY , HEALEY GORDON TERRY , RIDGWAY JOHN ANTHONY
Abstract: A jet nozzle assembly comprises a housing having a curved bearing surface which provides a seating for a complementary surface of a universally swivellable nozzle member through which in operation a propulsive jet may flow, an actuator for causing swivelling of the nozzle member relative to the housing, a conduit for supplying a cooling and/or lubricating fluid to the surfaces, a flange member secured to the nozzle member, and pressure responsive assembly for applying, in operation, hydrostatic pressure to the flange member so as to reduce or eliminate frictional opposition to its swivelling movement due to said propulsive jet.
Abstract translation: 喷射喷嘴组件包括具有弯曲支承表面的壳体，其提供通用旋转喷嘴构件的互补表面的座，通过所述喷嘴构件的可推动喷嘴可以在其中流动;用于使喷嘴构件相对于壳体旋转的致动器， 用于向表面供应冷却和/或润滑流体的导管，固定到喷嘴构件的凸缘构件和压力响应组件，用于在操作中向该凸缘构件施加静水压力，以便减少或消除与其对应的摩擦力 由于所述推进射流引起的旋转运动。
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Patent Agency Ranking
公开(公告)号：US3610534A
公开(公告)日：1971-10-05
申请号：US3610534D
申请日：1969-12-18
Applicant: ROHR CORP
Inventor： MEDAWAR GEORGE E , NELSON HAROLD E JR
CPC classification number: F02K1/60
Abstract: Each of a pair of thrust-reversing doors is mounted on an aircraft jet engine housing by means of four links, two of which are rotatable by gear drive mechanisms located at the points of connection of the links to the housing.
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公开(公告)号：US3570767A
公开(公告)日：1971-03-16
申请号：US3570767D
申请日：1969-10-01
Applicant: ROHR CORP
Inventor： LAWSON DALE W R , HOM FELIX , MOELLER RICHARD U
CPC classification number: F02K1/60
Abstract: Apparatus includes housing to rear of jet nozzle to surround the gas stream. Housing has openings in wall to receive thrust reverser doors which close openings in stowed position and swing to deployed thrust reverse position with trailing edges together. Doors diverge forwardly and leading edges are adjacent housing wall. Doors are curved about longitudinal axis and have end plates at leading edges to divert gas stream forwardly. Each end plate is divided into segments along leading edge pivoted thereto for swinging from parallel to perpendicular position. Segments are overlapped to move as a unit while accommodating curvature of door. In one form, segments are forced to open position by gas flow and returned to stowed position by bumper when doors close. In an another form, yoke within door actuated by movement of doors acts through force linkage to positively swing segments in each direction.
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公开(公告)号：US3486721A
公开(公告)日：1969-12-30
申请号：US74608868
申请日：1968-07-19
Applicant: VER FLUGTECHNISCHE WERKE
Inventor： MYCZINSKI ALFRED
CPC classification number: B64C29/0058 , B64C25/16 , B64C29/0091
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公开(公告)号：US3480236A
公开(公告)日：1969-11-25
申请号：US3480236D
申请日：1967-09-05
Applicant: GEN ELECTRIC
Inventor： NASH DUDLEY O
CPC classification number: F02K1/004
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公开(公告)号：US4185798A
公开(公告)日：1980-01-29
申请号：US885774
申请日：1978-03-13
Applicant: Robert Dickenson
Inventor： Robert Dickenson
CPC classification number: F02K1/605 , Y02T50/671
Abstract: A thrust reverser for a fan jet engine enclosed by an engine nacelle. The nacelle has a forward section fixed to the aircraft structure and a rearward translatable section attached to the forward section. The nacelle forming a secondary fan nozzle. A pair of blocker doors are pivotally attached to the rearward translatable nacelle section. Drag links are pivotally attached to the forward nacelle section and one of the drag link connects to each blocker door. A cascade ring is fixedly attached to the rear nacelle section and is translatable therewith for positioning within the opening between the nacelle portions when the rearward section is in a translated position. An air motor with drive connections to a plurality of ball-screw actuators provides the means for uniformly translating the rearward section. A recess in the inner surface of the rearward section is provided for the stowing of the links in a position out of the engine gas flow stream when the rearward section is in its stowed forward position.
Abstract translation: 用于由发动机机舱包围的风扇喷气发动机的推力反向器。 机舱具有固定到飞行器结构的前部和连接到前部的向后可平移部。 机舱形成二次风扇喷嘴。 一对阻挡门可枢转地附接到后向可平移的机舱部分。 拖动链接枢转地连接到前部机舱部分，其中一个拖动连杆连接到每个阻挡门。 级联环固定地附接到后机舱部分，并且当后向部分处于平移位置时，可与其平移以定位在机舱部分之间的开口内。 具有与多个滚珠丝杠致动器的驱动连接的气动马达提供了用于均匀地平移向后部分的装置。 在后部的内表面设有凹部，用于当后部处于其收起的正向位置时，将链节收集在发动机气流之外的位置。
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