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公开(公告)号：US20010001360A1
公开(公告)日：2001-05-24
申请号：US09757411
申请日：2001-01-09
IPC分类号： B63H011/00
CPC分类号： F02K9/95
摘要： The invention concerns an acoustic igniter for igniting a mixture of rocket fuels in a liquid propellant rocket engine combustion chamber comprising a cylindrical precombustion chamber (101) including a cylindrical wall (111) and first and second end walls (112, 113), a rocket fuel injection nozzle (103) emerging into the precombustion chamber (101) through the first end wall (112) via an orifice of diameter dn, a rocket fuel injector (104) arranged inside said nozzle (103) along the axis thereof, at least an outlet orifice (102) of minimum diameter df provided in the cylindrical wall (111), an acoustic resonator (105) defining a cavity opening into the precombustion chamber (101) opposite the nozzle (103), through the second end wall (113), via an orifice (151) of diameter dr. The acoustic resonator (105) is enclosed by a housing (106) which defines around the acoustic resonator (105) a closed auxiliary chamber (160) which communicates only with the precombustion chamber (101) by at least one conduit (107).
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公开(公告)号：US6118539A
公开(公告)日：2000-09-12
申请号：US470486
申请日：1999-12-22
申请人： Eric Gaumont , Michel Clement , Ayoub Chakari , Patrick Meyrueis
发明人： Eric Gaumont , Michel Clement , Ayoub Chakari , Patrick Meyrueis
摘要： An optical-fiber polarimetric sensor for measuring the displacement of an object relative to a frame, the sensor comprising a measurement optical fiber secured, over a fraction of its length, both to a central point of the object and to first and second fixed points of the frame, means disposed at one end of the measurement fiber and serving to emit a light beam of determined polarization into said measurement fiber, means for exerting twist on the measurement fiber so as to modify the polarization of the light beam, and means disposed at another end of the measurement fiber and serving firstly to detect the resulting light beam and secondly to determine the displacement of the object by analyzing the polarization modified in this way, wherein said measurement fiber is stripped, over said fraction of its length, of the covering that imparts mechanical strength thereto, and it is slid into a deformable guide sheath fixed both to the rotary object and also to the frame. Preferably, the deformable guide sheath is made of fine steel, and it may lined with a flexible protective sheath.
摘要翻译： 一种用于测量物体相对于框架的位移的光纤偏振传感器，所述传感器包括测量光纤，其测量光纤在其长度的一小部分上被固定到物体的中心点，并且固定到第一和第二固定点 所述框架，设置在所述测量光纤的一端并且用于将确定的偏振光发射到所述测量光纤中的装置，用于在所述测量光纤上施加扭曲以修改所述光束的偏振的装置，以及设置在 测量光纤的另一端，首先用于检测所得到的光束，其次通过分析以这种方式修改的偏振来确定物体的位移，其中所述测量光纤在其长度的所述部分上剥离覆盖物 其赋予机械强度，并且滑动到固定在旋转体上的可变形引导护套和框架。 优选地，可变形引导护套由精细钢制成，并且可以衬有柔性护套。
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公开(公告)号：US6029455A
公开(公告)日：2000-02-29
申请号：US919353
申请日：1997-08-28
申请人： Denis Sandelis
发明人： Denis Sandelis
CPC分类号： F23R3/002
摘要： A combustion chamber is disclosed for a turbojet engine in which the combustion chamber has a forward intake, a rear exit and a perforated casing extending between the intake and exit. The combustion chamber also has at least two rows of insulating tiles arrayed on the casing in forward and rear rows with both rows extending circumferentially around the inner surface of the casing bounding the combustion chamber. Each rear tile has a forward edge portion with a sloping wall and each forward tile has a tapered rear edge portion overlapping the forward edge portion with a clearance therebetween such that the tampered rear edge portion and the sloping wall bound a slot opening into the combustion chamber and slanting towards the rear of the combustion chamber to facilitate the formation of an air cooling film on inner surfaces of the tiles. The cooling air passes through the perforated casing, into the space between the casing and the tiles, through the clearance between the tiles and through the slot into the combustion chamber.
摘要翻译： 公开了一种用于涡轮喷气发动机的燃烧室，其中燃烧室具有前进气口，后出口和在进气口和出口之间延伸的穿孔壳体。 燃烧室还具有排列在前后两排的壳体上的至少两排绝缘砖，两排沿周向围绕着围绕燃烧室的壳体的内表面延伸。 每个后瓦片具有带有倾斜壁的前边缘部分，并且每个前瓦片具有与前边缘部分重叠的锥形后边缘部分，其间具有间隙，使得被篡改的后边缘部分和倾斜壁限定开口进入燃烧室 并且朝向燃烧室的后部倾斜以便于在瓷砖的内表面上形成空气冷却膜。 冷却空气穿过穿孔的壳体，穿过壳体和瓦片之间的空间，穿过瓦片之间的间隙并通过狭槽进入燃烧室。
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公开(公告)号：US5803433A
公开(公告)日：1998-09-08
申请号：US821335
申请日：1997-03-20
摘要： An apparatus for orienting the forces exerted by a helical coil spring on relatively movable elements is disclosed in which a movable element is movably mounted within a casing so as to move along a movement axis, in which a helical coil spring is interposed between the casing and the movable element so as to exert opposite forces on the casing and the movable element. The lateral forces and the torque forces on the movable element are eliminated by using a swivel joint interposed between the piston and one end of the helical coil spring. The use of the swivel element insures that the force exerted on the movable element by the helical coil spring is coincident with the movement axis of the movable element. A second swivel joint may be utilized between the second end of the helical coil spring and the casing, if desired.
摘要翻译： 公开了一种用于将由螺旋形螺旋弹簧施加的力定向在相对可移动元件上的装置，其中可移动元件可移动地安装在壳体内，以便沿着运动轴线移动，其中螺旋形螺旋弹簧介于壳体和 可移动元件以在壳体和可移动元件上施加相反的力。 通过使用插入在活塞和螺旋形螺旋弹簧的一端之间的旋转接头来消除可动元件上的横向力和扭矩力。 使用旋转元件确保由螺旋形螺旋弹簧施加在可移动元件上的力与可移动元件的移动轴线重合。 如果需要，可以在螺旋形螺旋弹簧的第二端和壳体之间使用第二旋转接头。
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公开(公告)号：US5598697A
公开(公告)日：1997-02-04
申请号：US505633
申请日：1995-07-21
IPC分类号： F23R3/00
CPC分类号： F23R3/002 , F05B2260/201 , F05B2260/202 , F05B2260/222
摘要： A wall structure for a wall bounding a combustion chamber of a gas turbine engine is disclosed having a first wall with an inner surface facing towards the interior of the combustion chamber and an outer surface facing away from the interior of the combustion chamber such that the inner surface forms a boundary of the combustion chamber and the outer surface has a surface roughness to prevent the formation of a fluid flow cooling layer which would cool the outer surface. The invention also has a second wall spaced from the outer surface of the first wall in a direction away from the interior of the combustion chamber so as to define a cooling fluid circulatory space between the first and second walls. A plurality of first perforations extend through the first wall in communication with the cooling fluid circulatory space to enable passage of cooling fluid from the space through the first perforations to form a cooling fluid film on the inner surface of the first wall.
摘要翻译： 公开了一种用于限定燃气涡轮发动机的燃烧室的壁的壁结构，其具有面向燃烧室内部的内表面的第一壁和远离燃烧室内部的外表面， 表面形成燃烧室的边界，并且外表面具有表面粗糙度，以防止形成冷却外表面的流体流动冷却层。 本发明还具有在远离燃烧室内部的方向上与第一壁的外表面隔开的第二壁，以便限定第一和第二壁之间的冷却流体循环空间。 多个第一穿孔延伸穿过与冷却流体循环空间连通的第一壁，以使冷却流体能够从空间通过第一穿孔，以在第一壁的内表面上形成冷却流体膜。
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公开(公告)号：US5470020A
公开(公告)日：1995-11-28
申请号：US319043
申请日：1994-10-06
CPC分类号： F02K1/123 , F02K1/1223 , F02K1/62 , F05D2250/323 , F05D2250/324 , F05D2250/33
摘要： A combination converging-diverging exhaust nozzle and thrust reverser for an aircraft turbojet engine is disclosed having a generally annular array of cold flaps extending from a downstream end of a cowling support structure and a generally annular, inner array of hot flaps, located radially inwardly of the cold flap array and extending downstream from an end of the hot gas exhaust duct. The annular array of hot gas flaps comprises two sets of hot flap arrays, an array of first hot flaps being pivotally attached to the downstream edge of the hot gas exhaust duct with the array of second hot flaps having upstream edges that are in contact with downstream edges of the array of first hot flaps. The positions of the arrays of the first and second hot flaps may be adjusted relative to a central longitudinal axis to form a converging-diverging nozzle with a variable cross-sectional area. The array of second hot flaps is also movable between a forward thrust position, wherein the upstream edges of the second hot flaps are urged into contact with the downstream edges of the first hot flaps and a reverse thrust position wherein the upstream edges of the second hot flaps are displaced away from the downstream edges of the first hot flaps. In the reverse thrust position, the downstream edges of the second hot flaps are in contact with each other so as to effectively block the exhaust gases and to redirect them in a direction which will induce a reverse thrust force onto the engine structure.
摘要翻译： 公开了一种用于飞行器涡轮喷气发动机的会聚发散排气喷嘴和推力反向器的组合，其具有从整流罩支撑结构的下游端和大体上环形的内部阵列的热襟翼延伸的大致环形阵列的冷襟翼， 冷翼阵列并且从热气体排气管的一端延伸到下游。 热气翼片的环形阵列包括两组热翼片阵列，第一热片阵列可枢转地附接到热气体排气管道的下游边缘，第二热片阵列具有与下游接触的上游边缘 第一热襟翼阵列的边缘。 可以相对于中心纵向轴线调节第一和第二热翼片的阵列的位置，以形成具有可变横截面积的会聚发散喷嘴。 第二热襟翼阵列也可以在前向推力位置之间移动，其中第二热襟翼的上游边缘被推动与第一热襟翼的下游边缘接触，并且反推力位置，其中第二热襟翼的上游边缘 襟翼从第一热襟翼的下游边缘移开。 在反向推力位置，第二热襟翼的下游边缘彼此接触，以便有效地阻挡废气并使它们朝向将引起反向推力的方向转向发动机结构。
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公开(公告)号：US5419360A
公开(公告)日：1995-05-30
申请号：US161259
申请日：1993-12-03
CPC分类号： G01M3/042 , F16L23/167 , Y10S116/07 , Y10T137/5762 , Y10T137/8326
摘要： A fluid supply system including a casing having at least one duct extending through it for the passage of fluid and a recess in the casing around the duct or ducts, a cover covering the recess and held against a bearing surface on the casing surrounding the recess, the cover carrying a continuation of the or each duct, and a vent in either the casing or the cover communicating the recess with the environment outside the casing, is provided with a leak tell-tale device for indicating passage of fluid along a path, such as the vent, which, in the event of a leakage of fluid from a duct into the recess, would be followed by the leaked fluid.
摘要翻译： 一种流体供应系统，包括：壳体，其具有至少一个延伸穿过其的管道，用于通过流体;以及在所述壳体中围绕所述管道或管道的凹部;覆盖所述凹部并保持在所述壳体周围所述凹部的支承表面上的盖， 所述盖承载所述或每个管道的延续部，以及将所述凹部与所述壳体外部的环境连通的所述壳体或所述盖中的通风口设置有用于指示流体沿着路径通过的泄漏指示装置， 作为排气口，在将流体从管道泄漏到凹槽中的情况下，泄漏的流体之后。
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公开(公告)号：US5398495A
公开(公告)日：1995-03-21
申请号：US228367
申请日：1994-04-15
CPC分类号： F23R3/26 , F05B2250/411
摘要： A generally annular combustion chamber for a gas turbine engine is disclosed having fuel injector assemblies, each with an oxidizer swirler, extending through an upstream end wall of the combustion chamber and control means connected to the control diaphragms of the oxidizer swirlers in order to move the control diaphragms between maximum and minimum flow positions. The upstream end wall of the combustion chamber defines complementary oxidizer intake orifices which have movable closure plates to selectively open or close the complementary oxidizer intake orifices. A mechanical linkage connects the closure plates to the control diaphragm of an adjacent air swirler such that, when the control diaphragms are in their maximum flow positions, the closure plates close the complementary oxidizer intake orifices, and when the control diaphragms are in their minimum flow positions, the closure plates are moved such that the complementary oxidizer intake orifices are fully open.
摘要翻译： 公开了一种用于燃气涡轮发动机的大体上环形的燃烧室，其具有燃料喷射器组件，每个燃料喷射器组件具有延伸通过燃烧室的上游端壁的氧化剂旋流器，以及连接到氧化器旋流器的控制膜片的控制装置， 在最大和最小流量位置之间控制隔膜。 燃烧室的上游端壁限定互补的氧化剂吸入口，其具有可移动的封闭板，以选择性地打开或关闭互补的氧化剂吸入口。 机械连杆将封闭板连接到相邻空气旋流器的控制膜片，使得当控制膜片处于其最大流动位置时，封闭板关闭互补氧化剂进气孔，并且当控制膜片处于其最小流量 位置，移动闭合板使得互补氧化剂吸入口完全打开。
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公开(公告)号：US5359851A
公开(公告)日：1994-11-01
申请号：US155217
申请日：1993-11-22
申请人： Pierre A. L. M. Bannerot , Guy J. Lapergue , Eric F. M. Maingre , Xavier J. Pasquali , Jean-Claude H. Reghezza
发明人： Pierre A. L. M. Bannerot , Guy J. Lapergue , Eric F. M. Maingre , Xavier J. Pasquali , Jean-Claude H. Reghezza
IPC分类号： F02K1/12
CPC分类号： F02K1/1292 , F02K1/1223
摘要： A variable geometry nozzle for a turbojet engine is disclosed wherein the adjustment of the cross-sectional area of the nozzle in a converging-diverging configuration is controlled by a single control system. The single control system varies the positions of both of the inner upstream and downstream flaps, as well as the outer flaps. A second control system operates simultaneously with the first control system to change the configuration of the nozzle to a converging-converging configuration. The inner, upstream flaps, which are pivotally connected to the downstream end of the turbojet exhaust duct, are controlled by an axially movable control ring which is connected to the controlled inner, upstream flaps via a link rod. The positions of the inner, downstream flaps, which have their upstream edges pivotally connected to a downstream edge of a corresponding upstream flap, are controlled by the movement of the upstream flap, as well as a connection with a cowling support via another link rod. The positions of the outer flaps are controlled by a cam which is operatively interposed between the control ring and the controlled, outer flaps.
摘要翻译： 公开了一种用于涡轮喷气发动机的可变几何喷嘴，其中以会聚发散构造的喷嘴的横截面面积的调节由单个控制系统控制。 单个控制系统改变内侧上游侧翼和下游侧翼以及外侧翼的位置。 第二控制系统与第一控制系统同时操作，以将喷嘴的配置改变为会聚会合配置。 枢转地连接到涡轮喷气排气管的下游端的内侧上游翼片由可轴向移动的控制环控制，所述控制环通过连杆连接到受控的内侧上游翼片。 通过上游翼片的运动以及通过另一连杆的与整流罩支架的连接来控制具有可枢转地连接到相应的上游翼片的下游边缘的其上游边缘的内侧和下游翼片的位置。 外片的位置由可操作地插入在控制环和受控的外翼之间的凸轮来控制。
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公开(公告)号：US5343619A
公开(公告)日：1994-09-06
申请号：US111892
申请日：1993-08-26
CPC分类号： F01D5/147 , Y10T29/49336
摘要： A hollow blade for a turbomachine comprises a unitary body having a multiplicity of transverse cavities in at least the airfoil shaped portion of the blade, and plugs disposed within the cavities and restoring the surface continuity of the intrados and extrados faces of the aerofoil shaped portion, the plugs being rigidly secured to the unitary body, such as by welding.
摘要翻译： 用于涡轮机的中空叶片包括在至少叶片的翼型部分中具有多个横向空腔的整体，以及设置在空腔内的塞子，并恢复翼型部分的内部和外侧面的表面连续性， 插头例如通过焊接被刚性地固定到整体上。
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