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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：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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3.发明授权Variable geometry flame trap device for use in an after-burner device of a gas turbine 失效用于燃气轮机的后燃烧器装置的可变几何形状的火焰捕集装置
公开(公告)号：US5269138A
公开(公告)日：1993-12-14
申请号：US16074
申请日：1993-02-10
CPC分类号： F23R3/22
摘要： A variable geometry flame trap device for use in an after-burner device of a gas turbine, which is not exposed to deformation forces during its use in the after-burner mode. This is achieved with a plurality of flame trap plate pairs (21), positioned downstream of the turbine at the outlet of a primary air flow duct (9) and mounted so as to pivot on a plurality of diffuser arms (19) located at the outlet of a secondary air flow duct (7), characterized in that the plates (21) of each pair are made from a composite material and in that they have a cam projecting from their facing faces (42), said two cams (43) bearing on one another.
摘要翻译： 一种用于燃气轮机的后燃烧器装置的可变几何型火焰捕集装置，其在后燃烧器模式中的使用期间不会受到变形力的影响。 这是通过多个阻气板对（21）来实现的，其位于涡轮机的主要空气流动管道（9）的出口的下游，并且安装成在位于所述主要空气流动管道（9）处的多个扩散器臂 二次气流管道（7）的出口，其特征在于，每对的板（21）由复合材料制成，并且它们具有从其相对面（42）突出的凸轮，所述两个凸轮（43） 彼此相依。
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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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5.发明授权Nozzle for a jet engine containing an adjustable convergent-divergent portion 失效用于喷气发动机的喷嘴，其包含可调节的收敛 - 发散部分
公开(公告)号：US5520336A
公开(公告)日：1996-05-28
申请号：US237399
申请日：1981-01-13
IPC分类号： F02K1/12
CPC分类号： F02K1/12 , F02K1/1223 , F05D2250/323 , F05D2250/324 , Y02T50/671
摘要： A nozzle comprises: a set of first flaps articulated to a rigid structure, and forming a convergent; a set of second flaps each articulated to a corresponding first flap, and forming a divergent; a set of third flaps each of which is connected at a position between two adjacent second flaps and which is, on the one hand, articulated to the rigid structure and, on the other hand, linked to each of the two adjacent second flaps by carrier linked to the aforesaid third flap by a ball joint.
摘要翻译： 喷嘴包括：一组铰接到刚性结构的第一翼片，并且形成会聚; 一组第二翼片，每个第二翼片铰接到相应的第一翼片，并形成发散; 一组第三翼片，每个翼片连接在两个相邻的第二翼片之间的位置，并且一方面铰接到刚性结构，另一方面通过载体连接到两个相邻的第二翼片中的每一个 通过球形接头连接到上述第三挡板。
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公开(公告)号：US4778109A
公开(公告)日：1988-10-18
申请号：US133886
申请日：1987-12-16
CPC分类号： F02K1/006 , F02K1/1223 , F02K1/1292 , F02K1/62
摘要： An adjustable two-dimensional nozzle is disclosed in which simplified control means are located away from the flow of gasses through the nozzle. The nozzle includes a movable frame located outside of fixed sidewalls and has pivotally attached thereto a pair of upstream or converging nozzle flaps. Upstream edges of the upstream flaps are attached to the movable frame such that the flaps pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. Downstream or diverging flaps are attached to the downstream edges of the upstream flaps such that these flaps also pivot about axes extending substantially perpendicular to the longitudinal axis of the nozzle. A cam member extends between each of the movable frames and each downstream flap to control the angular variations of the flaps during movement of the frame. The flap arrangements are symmetrically arranged with respect to a plane passing through the longitudinal axis of the nozzle, such that translational movement of the frames will alter the cross-section of the nozzle in a symmetrical manner with respect to the plane. If the frame is rotated about its pivot attachment, the nozzle flaps will be asymmetrically adjusted and may be utilized to vector the thrust of the gasses emanating from the nozzle.
摘要翻译： 公开了一种可调节的二维喷嘴，其中简化的控制装置位于远离气体流经喷嘴的位置。 喷嘴包括位于固定侧壁外侧的可移动框架，并且可旋转地附接有一对上游或会聚的喷嘴襟翼。 上游翼片的上游边缘附接到可移动框架，使得翼片围绕基本上垂直于喷嘴的纵向轴线延伸的轴线枢转。 下游或发散的翼片附接到上游翼片的下游边缘，使得这些翼片也围绕基本上垂直于喷嘴的纵向轴线延伸的轴线枢转。 凸轮构件在每个可移动框架和每个下游翼片之间延伸以在框架移动期间控制翼片的角度变化。 翼片装置相对于穿过喷嘴的纵向轴线的平面对称地布置，使得框架的平移运动将相对于平面以对称的方式改变喷嘴的横截面。 如果框架绕其枢轴附件旋转，则喷嘴挡板将被不对称地调节，并且可以用于对从喷嘴发出的气体的推力进行矢量化。
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公开(公告)号：US4679982A
公开(公告)日：1987-07-14
申请号：US773226
申请日：1985-09-06
IPC分类号： F04D27/02
CPC分类号： F04D27/0215 , F04D27/023
摘要： A ring or other annular assembly is supported within a compressor casing by means of one or more resiliently deformable bodies of elastomeric material adhered between two rigid plates. One of the rigid plates is secured to the ring, the other to the compressor casing, and both plates are disposed parallel to the direction of movement of the ring. Preferably, the resiliently deformable body is made up of an alternating stack of the elastomeric plates and rigid plates adhered together, and parallel with the first two rigid plates which secured the body to the ring and the casing. A compressor of a gas turbine plant incorporates an antisurge blow-off valve mechanism in the form of a slot formed in the outer wall defining the flow path and an annular assembly movable axially of the plant to close and open the slot.
摘要翻译： 环或其它环形组件通过粘附在两个刚性板之间的一个或多个弹性体材料的弹性变形体支撑在压缩机壳体内。 一个刚性板被固定到环上，另一个固定到压缩机壳体，并且两个板平行于环的移动方向设置。 优选地，弹性变形体由弹性体板和粘合在一起的刚性板的交替堆叠构成，并且平行于将主体固定到环和壳体上的前两个刚性板。 燃气轮机设备的压缩机包括形成在限定流路的外壁中的狭槽形式的防喘振排气阀机构，以及可移动到工厂轴向以闭合和打开槽的环形组件。
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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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9.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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