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公开(公告)号：US5542607A
公开(公告)日：1996-08-06
申请号：US448528
申请日：1982-11-24
IPC分类号： F02K1/12
CPC分类号： F02K1/1223 , F05D2250/323 , F05D2250/324 , Y02T50/671
摘要： A turbojet engine has an outlet duct to which an annular array of actuating cylinders for nozzle flaps are hinged. The housings for the cylinders are connected together by transverse members to form a rigid structure coaxial with the outlet duct. The arrangement includes convergent flaps and slaving devices for divergent flaps, all hinged to the rigid structure and particularly to the housings.
摘要翻译： 涡轮喷气发动机具有出口管道，用于喷嘴襟翼的致动气缸的环形阵列被铰接在该出口管道上。 用于气缸的壳体通过横向构件连接在一起以形成与出口管同轴的刚性结构。 该装置包括用于发散襟翼的会聚翼片和从动装置，其全部铰接于刚性结构，特别是铰接到外壳上。
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公开(公告)号：US5367874A
公开(公告)日：1994-11-29
申请号：US162879
申请日：1993-12-08
申请人： Didier L. C. Auffret , Gerard C. L. Berger , Eric Conete , Frederic Delage , Gerard E. A. Jourdain , Christophe J. F. Thorel
发明人： Didier L. C. Auffret , Gerard C. L. Berger , Eric Conete , Frederic Delage , Gerard E. A. Jourdain , Christophe J. F. Thorel
CPC分类号： F23R3/20
摘要： An integral, one-piece afterburner structure for a turbojet engine is disclosed which is formed of composite material. The afterburner structure has an outer casing formed as a body of revolution about a central axis, an inner casing also formed as a body of revolution about the central axis, which casings are integrally joined by a plurality of connecting arms extending between the inner and outer casing. The connecting arms are also formed of a composite material and are integrally molded with both the inner and outer casings. The afterburner structure also has a plurality of secondary support arms formed of composite material which extend either from the outer, or the inner casing in a generally radial direction relative to the central axis. Integrally formed with the plurality of secondary support arms is at least one annular flameholder ring which extends around the central axis and is supported by the secondary support arms.
摘要翻译： 公开了一种由复合材料形成的用于涡轮喷气发动机的整体式一体式加力结构。 所述加力结构具有外围壳体，所述外壳围绕中心轴线形成为旋转体，内壳体还围绕所述中心轴线形成为旋转体，所述壳体通过在所述内部和外部之间延伸的多个连接臂一体地连接 套管。 连接臂也由复合材料形成，并与内壳和外壳整体模制。 再加力结构还具有由复合材料形成的多个辅助支撑臂，其从外壳或内壳沿相对于中心轴线的大致径向方向延伸。 与多个第二支撑臂一体地形成有至少一个围绕中心轴线延伸并由第二支撑臂支撑的环形火焰支架环。
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公开(公告)号：US5421704A
公开(公告)日：1995-06-06
申请号：US258175
申请日：1994-06-10
申请人： Ollivier Carletti , Gerard F. Inizan , Gerard E. A. Jourdain , Francois M. P. Marlin , Philippe J. P. Pabion , Thierry G. Pancou , Laurence Prato , Dominique Raulin , Christine J. G. Ruffier
发明人： Ollivier Carletti , Gerard F. Inizan , Gerard E. A. Jourdain , Francois M. P. Marlin , Philippe J. P. Pabion , Thierry G. Pancou , Laurence Prato , Dominique Raulin , Christine J. G. Ruffier
CPC分类号： F01D5/282 , F01D11/008 , Y02T50/672 , Y02T50/673
摘要： A separate inter-blade platform for a turbomachine rotor comprises a structural rectilinear longitudinal member formed by a foam core, plies of a carbon/epoxy type material in bidirectional layers of crossed fibres oriented at 45.degree. laid around the core and around an insert at each end of the longitudinal member, each insert being made of juxtaposed radial plies of a carbon/epoxy type material in bidirectional layers of fibres crossed at .+-.45 degrees, and further plies of a carbon/epoxy type material in unidirectional layers oriented in the direction of the major axis of the longitudinal member covering the upper and lower faces of the member, the platform further comprising lateral packing cores made of a foam material, plies of a glass/epoxy type material covering the lateral faces of the longitudinal member and connecting it to the lateral foam cores, and peripheral plies of a glass/epoxy type material covering the assembly formed by the longitudinal member and the lateral cores connected thereto.
摘要翻译： 用于涡轮机转子的单独的叶片间平台包括由泡沫芯构成的结构直线纵向构件，碳/环氧树脂型材料层，横向纤维的双向层中的45°铺绕在芯周围，并且在每个位置处围绕插入件 纵向构件的端部，每个插入件由在+/- 45度交叉的双向纤维层中的碳/环氧树脂型材料的并置径向层制成，并且在单向层中定向的另外的碳/环氧树脂类材料层 纵向构件的主轴的方向覆盖构件的上表面和下表面，平台还包括由泡沫材料制成的侧包装芯，玻璃/环氧树脂类材料层覆盖纵向构件的侧面并连接 侧向泡沫芯和覆盖由纵向构件和侧向芯c形成的组件的玻璃/环氧树脂类型的外围层 连接到其上。
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公开(公告)号：US5359849A
公开(公告)日：1994-11-01
申请号：US162883
申请日：1993-12-08
申请人： Didier L. C. Auffret , Gerard C. L. Berger , Eric Conete , Frederic Delage , Gerard E. A. Jourdain , Christophe J. F. Thorel
发明人： Didier L. C. Auffret , Gerard C. L. Berger , Eric Conete , Frederic Delage , Gerard E. A. Jourdain , Christophe J. F. Thorel
CPC分类号： F23R3/18
摘要： An afterburner assembly is disclosed in which the flameholder ring is for by plurality of flameholder ring segments, each segment being integrally formed with a generally radially extending arm. The flameholder ring segments extend beyond each opposite sides of the arm. The arm and flameholder ring segments are attached to the casing of the afterburner by a support element which is pivotally attached to the arm and fixedly attached to the afterburner casing. The distal end of the arm slidably contacts the casing defining the opposite side of the afterburner duct to enable the arm to slide relative to the casing to allow for differential thermal expansion of the respective elements. When each of the arm/flameholder ring segments are attached to the afterburner casing, the flameholder ring segments form a generally annular flameholder ring. The ring has a generally "U"-shaped cross-sectional configuration with the legs of the "U"-shape extending generally parallel to a central axis and opening in a downstream direction according to the gas flow flowing through the afterburner duct.
摘要翻译： 公开了一种加力燃烧器组件，其中火焰稳定器环由多个火焰稳定器环段形成，每个段与大致径向延伸的臂一体地形成。 火焰稳定器环段延伸超过臂的每个相对侧。 臂和火焰稳定器环段通过支撑元件附接到加力器的壳体，该支撑元件枢转地附接到臂并且固定地附接到加力器壳体。 臂的远端可滑动地接触限定加力器管道相对侧的壳体，以使臂相对于壳体滑动以允许各个元件的差分热膨胀。 当每个臂/火焰稳定器环段连接到加力燃烧器壳体时，火焰稳定器环段形成大致环形的火焰稳定器环。 环具有大致“U”形横截面形状，其中“U”形的腿基本上平行于中心轴延伸并且根据流过加力管的气流沿下游方向开口。
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5.发明授权Heat protective lining for an afterburner or transition duct of a turbojet engine 失效涡轮发动机燃烧器或过渡管的保护衬里
公开(公告)号：US5069034A
公开(公告)日：1991-12-03
申请号：US521036
申请日：1990-05-08
CPC分类号： F23R3/002 , F02K1/822 , F23R3/60 , F05D2250/34 , Y02T50/672 , Y02T50/675
摘要： A heat protective lining for the afterburner or transition duct of a turbojet engine comprises an assembly of tiles overlapping laterally and longitudinally to form overlapping rings of tiles in which the tiles of each ring are offset laterally from those of each adjacent ring by half a tile width. The tiles are held together by eyelets projecting from the overlapped downstream portions of the tiles through apertures in the overlapping upstream portions, and locking members engaging through the eyelets. Fastening yokes for fixing the assembly to the duct casing are secured to the outside of the tiles.
摘要翻译： 用于涡轮喷气发动机的后燃器或过渡管道的保护衬里包括横向和纵向重叠的瓦片组合，以形成瓦片的重叠环，其中每个环的瓦片横向偏离每个相邻环件的瓦片半块宽度 。 瓦片通过在重叠的上游部分中的孔从突出的瓦片的下游部分突出的孔眼保持在一起，并且锁定构件通过孔眼接合。 用于将组件固定到管壳的紧固轭被固定到瓦的外部。
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公开(公告)号：US4817871A
公开(公告)日：1989-04-04
申请号：US215257
申请日：1988-07-05
CPC分类号： F02K1/1223 , F02K1/12 , F05D2250/323 , F05D2250/324 , F05D2250/33 , Y02T50/671
摘要： The system according to the invention has an annular array of converging flaps, diverging flaps and cold flaps attached to the downstream edge of the turbojet engine exhaust duct by several pairs of longitudinally extending support beams. The pairs of beams are interconnected and the flap actuators are located between such interconnected pairs of support beams. The control system has a plurality of generally straight control shafts extending around the circumference of the converging and diverging flaps. The control shafts are interconnected with the actuators, the support beams, the diverging flaps and the cold flaps to ensure that the flaps are synchronously adjusted to their desired positions. Triangularly shaped link members are attached to each end of the control shafts and serve to interconnect adjacent shafts. A base of each of the link members is pivotally attached to an end of the control shaft, while a universal-type ball joint interconnects the adjacent apexes of the triangular link members.
摘要翻译： 根据本发明的系统具有通过几对纵向延伸的支撑梁连接到涡轮喷气发动机排气管道的下游边缘的会聚翼片，发散翼片和冷襟翼的环形阵列。 梁对被互连并且翼片致动器位于这样互连的支撑梁对之间。 控制系统具有多个大致直线的控制轴，其围绕会聚和发散的襟翼的圆周延伸。 控制轴与致动器，支撑梁，发散翼片和冷襟翼互连，以确保襟翼被同步调整到其所需的位置。 三角形连杆构件连接到控制轴的每一端并用于连接相邻的轴。 每个连接构件的基部可枢转地附接到控制轴的端部，而通用型球窝接头将三角形连杆构件的相邻顶点互连。
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公开(公告)号：US4565492A
公开(公告)日：1986-01-21
申请号：US628311
申请日：1984-07-06
CPC分类号： F01D11/18 , Y02T50/671
摘要： A sealing device is disclosed for maintaining a small positive clearance between packing segments and the turbine blade tips of a turbojet engine. The packing segments are connected to an inner ring which is, in turn, connected to an outer ring, all disposed within the turbojet casing. The coefficient of thermal expansion of the inner ring is greater than that of the outer ring such that, as air is directed onto the structure from the engine compressor, the differential expansion or contraction of the rings serves to move the packing segment in a radial direction to maintain the clearance between them and the turbine blade tips.
摘要翻译： 公开了一种密封装置，用于在涡轮喷气发动机的包装段和涡轮叶片尖之间保持小的正间隙。 包装段连接到内环，该内环又连接到外环，全部设置在涡轮喷气发动机外壳内。 内圈的热膨胀系数大于外圈的热膨胀系数，使得当空气从发动机压缩机引导到结构体上时，环的差动膨胀或收缩用于沿着径向移动包装段 以保持它们与涡轮叶片尖端之间的间隙。
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公开(公告)号：US4541567A
公开(公告)日：1985-09-17
申请号：US502203
申请日：1983-06-08
CPC分类号： F02K1/12 , Y10S60/905
摘要： A vane for a convergent-divergent nozzle is constituted by a central body d a base plate. The central body comprises a reinforcement substantially in the shape of an isoceles triangle and of channel section, the reinforcement having internal and external edge flanges and a cover plate of the same shape and dimensions as the reinforcement, the reinforcement being secured to the flanges of the latter.The base plate is rectangular and has a triangular opening of a contour corresponding to that of the reinforcement. The central body is secured to the base plate by securing means constituted by a profiled member of a shape corresponding to that of the opening.The central body is of a composite carbon-carbon material; the base plate and securing means, of steel.
摘要翻译： 收敛发散喷嘴的叶片由中心体和基板构成。 中心体包括基本上等间距三角形和通道部分形状的加强件，该加强件具有内部和外部边缘凸缘以及与加强件相同形状和尺寸的盖板，该加强件固定到该凸缘的凸缘上 后者。 基板是矩形的，具有与加强件相对应的轮廓的三角形开口。 中心体通过由与开口相对应的形状的成形构件构成的固定装置固定在基板上。 中心体为复合碳 - 碳材料; 基板和固定装置。
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公开(公告)号：US5623821A
公开(公告)日：1997-04-29
申请号：US509054
申请日：1995-07-31
CPC分类号： H05B6/80 , B64D33/02 , F02C7/047 , B64D2033/0233 , B64D2033/0286 , H05B2214/02 , Y02T50/672
摘要： A turbojet having an air intake case including radial arms between an outer annular structure and an inner central structure, and a deicing unit configured to deice the radial arms by microwaves and located in the central structure. The deicing unit has a microwave generator and a transmitting element configured to transmit energy and including an inside annular waveguide located inside of the central structure. An energy distributing element configured to eliminate ice is coupled with the transmitting element by a coupling element. The radial arms are made from a dielectric composite material.
摘要翻译： 一种具有进气口的涡轮喷气发动机，其包括位于外部环形结构和内部中心结构之间的径向臂，以及除冰单元，其构造成通过微波来定位径向臂并且位于中心结构中。 除冰单元具有微波发生器和发送元件，其被配置为传输能量并且包括位于中心结构内部的内部环形波导。 配置成消除冰的能量分配元件通过耦合元件与发射元件耦合。 径向臂由介电复合材料制成。
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公开(公告)号：US5566884A
公开(公告)日：1996-10-22
申请号：US336491
申请日：1981-12-30
IPC分类号： F02K1/12
CPC分类号： F02K1/1223 , F05D2250/323 , F05D2250/324 , Y02T50/671
摘要： Convergent flaps of a jet engine nozzle are controlled by actuating cylinders through actuating levers hinged to the fixed structure of the engine and by connecting rods. Divergent flaps are slaved to the convergent flaps by connecting rods themselves driven by the actuating levers. Cold flaps not hinged to the divergent flaps are slaved to the convergent flaps by further connecting rods connected to the first-named connecting rods.
摘要翻译： 喷气发动机喷嘴的收敛翼片通过致动液压缸通过铰链到发动机的固定结构的致动杆和通过连接杆来控制。 通过由致动杆驱动的连接杆本身，不同的翼片从收敛的翼片中被切割。 通过连接到第一个连接杆的另外的连接杆，不铰接到发散的翼片的冷襟翼被奴隶到收敛的襟翼。
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