公开(公告)号：US5078341A

公开(公告)日：1992-01-07

申请号：US671120

申请日：1991-03-18

申请人： Bartholomaus Bichler ,  Michael Jost

发明人： Bartholomaus Bichler ,  Michael Jost

IPC分类号： B64D33/02 ,  F02C7/042

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/026 ,  Y02T50/672 ,  Y10T137/0536

摘要： An hydraulically-pivotable inlet ramp with box-like shaped cross-section for supplying air into engines of supersonic or hypersonic airplanes. The inlet ramp, comprised of a plurality of relatively movable elements, can be adjusted into a number of different positions to optimize air flow under various mach conditions, as well as control a boundary air layer inlet.

摘要翻译： 一个液压可枢转的入口斜坡，具有盒状截面，用于将空气供给超音速或超音速飞机的发动机。 包括多个相对可移动元件的入口斜面可以被调节成多个不同的位置，以优化在各种马达条件下的空气流动，以及控制边界空气层入口。

公开(公告)号：US5005782A

公开(公告)日：1991-04-09

申请号：US386130

申请日：1989-07-28

申请人： Francois Falempin ,  Claude Sans ,  Champigny Patrick ,  Gerard Laruelle ,  Jean-Marie Garrel

发明人： Francois Falempin ,  Claude Sans ,  Champigny Patrick ,  Gerard Laruelle ,  Jean-Marie Garrel

IPC分类号： B64D33/02 ,  F02C7/042

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/026 ,  Y10T137/0536

摘要： A two dimensional supersonic air intake is provided for the combustion airf an aircraft engine comprising on one side a front flap (3) forming a visor and on the other side a fairing (4). The front flap (3) is movable about a pivoting axis (5) situated opposite the fairing (4). The front flap (3) is fast with a mobile fairing nose (6) situated in front of fairing (4) and moving in front of the latter when the front flap (3) moves in the direction which increases the air intake section.

摘要翻译： 为飞机发动机的燃烧空气提供二维超音速进气口，其包括在一侧形成形成遮阳板的前挡板（3），另一侧上设有整流罩（4）。 前挡板（3）可围绕位于整流罩（4）相对的枢转轴线（5）移动。 前挡板（3）在位于整流罩（4）前方的移动整流罩（6）上，当前挡板（3）沿增加进气部分的方向移动时，前挡板（3）快速移动。

公开(公告)号：US4991795A

公开(公告)日：1991-02-12

申请号：US298117

申请日：1989-01-17

申请人： Joseph L. Koncsek

发明人： Joseph L. Koncsek

IPC分类号： B64D33/02 ,  F02C7/042

CPC分类号： B64D33/02 ,  F02C7/042 ,  B64D2033/026 ,  Y10T137/0536

摘要： A mixed compression inlet having a forward ramp, an aft ramp, and a slot therebetween is disclosed. The aft ramp is coupled to the inlet to permit both fore-aft movement and rotational movement. The geometric throat of the inlet is located at the leading edge of the aft ramp. The slot opens into a plenum chamber. A vent permits air to exit from the plenum chamber. The pressure in the plenum chamber is maintained approximately equal to the pressure on the aft portion of the forward ramp. A servocontroller receiving input from pressure sensors of the forward ramp and in the plenum chamber controls the position of a vent door to ensure that the proper pressure is maintained within the plenum chamber.

摘要翻译： 公开了一种混合压缩入口，其具有正斜面，后斜面和它们之间的狭槽。 后斜坡联接到入口以允许前后运动和旋转运动。 入口的几何喉部位于后斜坡的前缘。 狭槽开口进入增压室。 通风口允许空气从增压室排出。 增压室中的压力保持近似等于前进斜坡后部的压力。 接收来自正向斜坡的压力传感器和增压室的输入的伺服控制器控制通风门的位置，以确保在通风室内保持适当的压力。

公开(公告)号：US4865268A

公开(公告)日：1989-09-12

申请号：US209193

申请日：1988-06-20

申请人： Peter Tracksdorf

发明人： Peter Tracksdorf

IPC分类号： B64D33/02 ,  F02C7/042

CPC分类号： B64D33/02 ,  F02C7/042 ,  B64D2033/0286 ,  Y02T50/671 ,  Y10T137/0645

摘要： A construction is provided to aerodynamically affect a jet engine nacelle in its intake lip area primarily by forming and pivotally arranging flaps on a radially outer circumferential sector of the intake lip such that from a first extreme position, in which they are adapted to a cruise lip geometry, they can be moved into a second extreme position, in which they radially expand the outer contour of the intake lip while providing and exposing air blowoff ducts with their rear side, said ducts terminating at the outer wall of the nacelle at essentially a tangent therewith. Further air injection flaps are also provided in certain embodiments for forming air injection ducts through the intake lip walls during certain engine operating conditions.

摘要翻译： 提供了一种结构，其空气动力学地影响其进气口区域中的喷气发动机机舱，主要通过在进气口的径向外圆周区段上形成和枢转地布置翼片，使得从第一极限位置，它们适合于巡航唇 几何形状，它们可以移动到第二极限位置，在该第二极限位置，它们径向地扩大进气口的外轮廓，同时提供和暴露空气吹出管道与其后侧，所述导管终止在机舱的外壁上，基本上是切线 随之而来。 在某些实施例中还提供了另外的空气注入挡板，用于在某些发动机操作条件期间通过进气口壁形成空气喷射管道。

公开(公告)号：US4418708A

公开(公告)日：1983-12-06

申请号：US239021

申请日：1981-02-24

申请人： Carsten Schulze ,  Kurt Lotter ,  Jakob Malefakis

发明人： Carsten Schulze ,  Kurt Lotter ,  Jakob Malefakis

IPC分类号： F02C7/042

CPC分类号： F02C7/042 ,  F05D2200/15 ,  Y10T137/0645

摘要： A two-dimensional, unidirectional oblique air impact diffuser is used as an air inlet for a gas turbine jet engine for aircraft. The air inlet includes an upper rigid air inlet ramp and an air inlet bottom spaced below the ramp. An air scoop lip is pivotally attached to the air inlet bottom so that it can be pivoted from a standard setting point downwardly away from the air inlet ramp and also from the standard setting point toward the ramp. The pivotal displacement of the air scoop lip is a function of the aircraft angle of attack and the flight Mach number. The angular displacement of the air scoop lip from the standard setting point increases downwardly as the aircraft angle of attack increases and decreases as the Mach number increases.

摘要翻译： 二维单向倾斜空气冲击扩散器用作飞机燃气轮机喷气发动机的进气口。 空气入口包括上部刚性空气入口斜坡和在斜坡下方间隔开的空气入口底部。 空气勺唇可枢转地附接到进气口底部，使得其可以从标准设定点向下远离空气入口斜坡以及从标准设定点向斜坡枢转。 空气勺唇的关键位移是飞机迎角和飞行马赫数的函数。 空气勺唇从标准设定点的角位移随着飞机迎角增加而减小，随着马赫数增加。

公开(公告)号：US3998048A

公开(公告)日：1976-12-21

申请号：US521660

申请日：1974-11-07

申请人： Anicet Derue

发明人： Anicet Derue

IPC分类号： B64D33/02 ,  F02C7/042 ,  F02C7/05 ,  F02C7/052 ,  F02C7/055 ,  F02C7/04

CPC分类号： F02C7/042 ,  B64D33/02 ,  F02C7/052 ,  B64D2033/0246 ,  B64D2033/0293 ,  Y02T50/672

摘要： The invention relates to equipment for the air intake of an aircraft turbine engine, which equipment includes an inlet duct capable of being obturated by a bullet therein, and a bullet thrust mechanism connected to the duct by studs forming bullet guides. Part of the duct is formed by box members for receiving a plurality of separating elements downstream of deflectors, the internal face of the duct lip together with the external face of the bullet and of a jack piston and cylinder of said thrust mechanism being made of soundproofing material.

摘要翻译： 本发明涉及一种用于飞行器涡轮发动机的进气的设备，该设备包括能够通过其中的子弹密封的入口管道，以及通过形成子弹引导件的螺柱连接到管道的子弹推力机构。 管道的一部分由用于在偏转器下游接收多个分离元件的盒构件形成，管道唇缘的内表面与子弹的外表面以及所述推力机构的千斤顶活塞和气缸由隔音构成 材料。

公开(公告)号：US3915413A

公开(公告)日：1975-10-28

申请号：US45475174

申请日：1974-03-25

申请人： GEN ELECTRIC

发明人： SARGISSON DONALD FARLEY

IPC分类号： B64D33/02 ,  F02C7/042 ,  B64D29/00

CPC分类号： B64D33/02 ,  B64D2033/026 ,  F02C7/042 ,  F05D2220/80 ,  Y02T50/671 ,  Y10T137/0645

摘要： A variable geometry inlet system is provided for a subsonic/supersonic gas turbine engine wherein a secondary inlet airflow is selectively ejected into a primary inlet airflow in order to augment the overall mass airflow to the engine and increase inlet pressure recovery. A plurality of foils are cooperatively disposed in rotatable connection with respect to a nacelle in order to modulate the secondary inlet airflow and match the velocity of the secondary airstream to that of the primary airstream thus reducing the mixing loss which would otherwise occur if the two streams commingled at different velocities. The primary and secondary inlet airstreams may also be maintained at a sufficiently high velocity to reduce the forward propagation of engine generated noise. The foils may also be rotated to define an outlet whereby a portion of the primary inlet airflow may be ejected overboard during supersonic operation to reduce aerodynamic drag as might otherwise result from a malfunctioning engine.

摘要翻译： 提供了用于亚音速/超音速燃气涡轮发动机的可变几何入口系统，其中次级入口气流被选择性地喷射到主入口气流中，以便增加到发动机的总质量气流并增加入口压力恢复。 多个箔片相对于机舱以可旋转的方式相互配合地设置，以便调节次级入口气流并使二次气流的速度与主要气流的速度相匹配，从而减少如果两个流 混合在不同的速度。 主入口气流和次级入口气流也可以以足够高的速度保持，以减少发动机产生的噪声的正向传播。 箔也可以旋转以限定出口，由此在超音速操作期间，主入口气流的一部分可能被外侧喷射，以减少否则可能由故障发动机引起的气动阻力。

公开(公告)号：US3770228A

公开(公告)日：1973-11-06

申请号：US3770228D

申请日：1971-12-08

申请人： LOCKHEED AIRCRAFT CORP

发明人： TRAKSEL J ,  DUPCAK J

IPC分类号： B64D33/02 ,  F02C7/042 ,  B64D29/00

CPC分类号： F02C7/042 ,  B64D33/02 ,  B64D2033/0286 ,  Y02T50/671 ,  Y10T137/0536

摘要： A series of inlet fences or spoilers carried on the nacelle of an aircraft turbine engine which are used to selectively divert streamlines which would otherwise become detached at the inlet lip. This selectively variable air-inlet geometry provides for minimum drag during cruise and yet obviates engine surge or stall or other effects detrimental to the engine which could otherwise occur on the ground and at low forward velocity when crosswinds combine with high engine power demands.

摘要翻译： 在飞机涡轮发动机的机舱上承载的一系列入口围栏或扰流板，其用于选择性地转移将在入口唇缘处分离的流线。 这种选择性可变的进气口几何形状在巡航期间提供最小的阻力，并且避免发动机喘振或失速或其他对发动机有害的影响，否则当侧风与高发动机功率需求相结合时，可能会在地面上以低速向前速度发生。

公开(公告)号：US3719428A

公开(公告)日：1973-03-06

申请号：US3719428D

申请日：1970-03-13

申请人： DETTMERING W

发明人： DETTMERING W

IPC分类号： F02C7/04 ,  F02C7/042 ,  F01D1/02 ,  F02K3/00

CPC分类号： F02C7/042 ,  F02C7/04 ,  F05D2200/262 ,  Y02T50/671

摘要： A jet engine, which is suited for hypersonic intake velocities, has a rotating cascade in the intake duct for decelerating the hypersonic flow. The blade angles Beta 1, Beta 2 of the rotating cascade, the circumferential speed U of the rotor and the deceleration Delta w of the relative cascade flow are matched in accordance with cos Beta 2 (U . cos Beta 1)/(U Delta W . cos Beta 1), to ensure an axial direction of the absolute flow at the rotor cascade exit. A stationary vane cascade can be arranged downstream of the rotor cascade, in the case of high blade camber, for further deceleration and axial straightening of the flow. The intake rotor can be coupled to an engine accessory power unit or to a compressor arranged downstream of the intake. Controllable flaps can be provided to route the gas jet leaving the engine combustion chamber either to a turbine arranged downstream for driving the compressor or directly to the engine outlet nozzle. The intake rotor can also be coupled to an acceleration cascade arranged downstream of the combustion chamber; the acceleration cascade can also be preceded by a stationary vane cascade.

摘要翻译： 适用于超音速进气速度的喷气发动机在进气管中具有旋转级联，用于减速超音速流。 旋转级联的叶片角度β1，β2，转子的圆周速度U和相对级联流的减速度DELTA w根据cosβ2 =（U·cosβ1）/（U- DELTA W。cosβ1），以确保转子级联出口处的绝对流动的轴向。 在高叶片外倾的情况下，可以在转子级联的下游布置固定叶片级联，以进一步减速和流动的轴向矫直。 进气转子可以联接到发动机附件动力单元或布置在进气口下游的压缩机。 可以提供可控翼片以将离开发动机燃烧室的气体射流引导到布置在下游的涡轮机，用于驱动压缩机或直接驱动到发动机出口喷嘴。 进气转子还可以耦合到布置在燃烧室下游的加速级联; 加速级联也可以在固定叶片级联之前。

公开(公告)号：US3667704A

公开(公告)日：1972-06-06

申请号：US3667704D

申请日：1970-05-05

申请人： MESSERSCHMITT BOELKOW BLOHM

发明人： ASSMANN KARL H

IPC分类号： B64D33/02 ,  F02C7/042

CPC分类号： B64D33/02 ,  B64D2033/022 ,  B64D2033/026 ,  F02C7/042 ,  Y10T137/0536

摘要： DOOR FOR THE AIR INTAKE DUCT OF AUXILIARY ENGINE OF JET AIRCRAFT. THE DOOR IS PIVOTALLY MOUNTED AT THE FORWARD END OF TH ERECESS IN THE FUSELAGE WHICH RECESS IS NORMALLY PROVIDED AND ALIGNED WITH THE AIR INTAKE DUCT FOR THE AUXILIARY ENGINE. IN OPEN POSITION THE DOOR SURFACES ARE ALIGNED WITH THE SURFACES OF THE AUXILIARY AIR INTAKE DUCT WHILE IN CLOSED POSITION THE DOOR PROVIDES A SURFACE ALIGNED WITH THE INNER SURFACE OF THE MAIN AIR INTAKE DUCT.

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