-
公开(公告)号：US4863354A
公开(公告)日：1989-09-05
申请号：US253760
申请日：1988-10-05
CPC分类号： B64C11/14 , F02C7/047 , F05D2200/221 , Y02T50/672
摘要： A nose cowl or spinner is provided for a fixed, non-rotatable central hub of a turbojet engine having assembly means that facilitate the attachment and detachment of the nose cowl to the central hub, and provides a readily visible indication of whether or not the nose cowl has been properly assembled to the hub. The nose cowl has a smooth outer surface to provide undisturbed air flow into the turbojet engine compressor and defines means to circulate heated air to prevent icing of the external surface. An inner cowl member is attached to a bearing cover of the central hub in a non-rotatable manner, an outer cowl member is axially locked to the central hub so as to be concentrally arranged about the inner cowl member, and a locking device is used to lock the inner and outer cowl members together to prevent inadvertent rotation of the outer cowl member.
摘要翻译： 提供了一种用于涡轮喷气发动机的固定的，不可旋转的中心轮毂的鼻罩或旋转器，其具有便于将鼻罩安装和拆卸到中心轮毂的组装装置，并且提供了鼻子 整流罩已正确组装到集线器。 鼻罩具有光滑的外表面，以提供未受干扰的空气流入涡轮喷气发动机压缩机，并且限定了循环加热空气以防止外表面结冰的装置。 内罩壳部件以不可旋转的方式附接到中心轮毂的轴承盖上，外整流罩部件轴向地锁定到中心轮毂，以便围绕内整流罩部件同心地布置，并且使用锁定装置 以将内外罩组件锁定在一起以防止外罩组件的意外旋转。
-
公开(公告)号：US4320903A
公开(公告)日：1982-03-23
申请号：US79433
申请日：1979-09-27
CPC分类号： F01D25/12 , F01D11/02 , F02C7/12 , F02C7/18 , F02C7/28 , Y02T50/675 , Y10S277/931
摘要： A labyrinth seal mounted between a shaft and the casing of a gas turbine combustion chamber, wherein the support of an abradable sealing surface in the seal which operates in conjunction with rapidly rotating fins is cooled by an upstream airflow parallel to the envelope surface of the extremities of such fins and opening into an upstream space. The cooling air is taken in from the casing by means of a conduit which is connected with an overflow valve tied to the gas turbine load. The invention is applicable to aviation turbojets.
摘要翻译： 安装在轴和燃气轮机燃烧室的壳体之间的迷宫式密封件，其中密封件中可磨损的密封表面的支撑件与快速旋转的翅片结合起来，其通过平行于末端的包络面的上游气流来冷却 的这种翅片并打开到上游空间。 冷却空气通过与连接到燃气轮机负载的溢流阀连接的导管从壳体中吸入。 本发明适用于航空涡轮喷气发动机。
-
公开(公告)号：US5622472A
公开(公告)日：1997-04-22
申请号：US571729
申请日：1995-12-13
申请人： Pierre A. Glowacki
发明人： Pierre A. Glowacki
CPC分类号： F01D21/045
摘要： Protective shield (9) for a turbo-engine external fairing (3). It comprises a ring made of a ductile material retained by several fastening means relatively easy to break. When a rotor portion (17) accidentally detached strikes it, it dents it breaking some or all of its fasteners. By means of this possibility allowing for wide deformations of the shield (9), the capacity for absorbing energy is significant.
摘要翻译： 用于涡轮发动机外部整流罩（3）的防护罩（9）。 它包括由相对容易断裂的几个紧固装置保持的延性材料制成的环。 当转子部分（17）意外地分离时，它打破其部分或全部的紧固件。 通过这种可能性允许屏蔽（9）的宽变形，吸收能量的能力是显着的。
-
公开(公告)号：US5145319A
公开(公告)日：1992-09-08
申请号：US616594
申请日：1990-11-21
申请人： Pierre A. Glowacki
发明人： Pierre A. Glowacki
IPC分类号： F01D5/30
CPC分类号： F01D5/3053
摘要： An axial flow turbomachine rotor comprises a disc having a plurality of annular flanges extending outwardly from its periphery, a plurality of blades secured to the disc and extending radially outwardly from the periphery thereof, each of the blades having its root notched to define heels which are received in the grooves formed between the annular flanges of the disc, and a plurality of separate platforms which are secured to the disc and are disposed between the blades to define the inner boundary of the fluid flow path through the rotor, the blades each being fixed to the disc by two parallel pins which are equidistance from the axis of the disc and are received in corresponding bores passing through the annular flanges and the heels of the blade, the pins also serving to secure the platforms to the disc.
摘要翻译： 轴流式涡轮机转子包括具有从其周边向外延伸的多个环形凸缘的盘，多个叶片，其固定到盘上并从其周边径向向外延伸，每个叶片的根部被切口以限定高度 容纳在形成在盘的环形凸缘之间的凹槽中，以及多个单独的平台，其固定到盘上并且设置在叶片之间以限定通过转子的流体流动路径的内边界，叶片各自固定 通过与盘的轴线等距的两个平行的销钉接收到盘上，并且被接收在穿过环形凸缘和叶片的高跟的对应的孔中，销还用于将平台固定到盘上。
-
公开(公告)号：US4222706A
公开(公告)日：1980-09-16
申请号：US929908
申请日：1978-08-01
IPC分类号： F01D11/08
CPC分类号： F01D11/08
摘要： A turbine housing for a jet engine is provided with a ring of an abradableorous material. A supporting and mounting device consisting of a cylindricoconical monoblock having a conical internal jacket provides for the convection cooling of the external surface and a cylindrical jacket for cooling air is held over the abradable ring by means of a perforated ferrule integral with the rest of the device. The abradable ring carries transverse partitions to prevent axial leakage.
摘要翻译： 用于喷气发动机的涡轮壳体设置有耐磨多孔材料的环。 由具有锥形内套的圆柱形整体构成的支撑和安装装置提供外表面的对流冷却，并且用于冷却空气的圆柱形护套通过与该装置的其余部分成一体的多孔套圈保持在可磨损环上 。 耐磨环承载横向隔板以防止轴向泄漏。
-
公开(公告)号：US4870826A
公开(公告)日：1989-10-03
申请号：US203765
申请日：1988-06-08
CPC分类号： F23R3/283 , F02C6/08 , F04D29/542 , F04D27/023
摘要： A casing structure for an annular combustion chamber of a turbojet engine is disclosed in which air is tapped from an upstream end portion of the casing, while at the same time preventing contamination of such tapped air from the injected fuel. The casing has annular inner and outer walls disposed on either side of the combustion chamber. The casing has an upstream end which is attached to the downstream end of the exhaust gas turbine. The outer annular casing wall defines circumferentially spaced apart fuel injector orifices and circumferentially spaced apart air tapping orifices which are circumferentially alternating with the fuel injector orifices. A partition wall extending between an air diffuser and the inner surface of the outer annular wall divides the radial space separating the diffuser and the outer annular wall into first cavities which communicate with the air tapping orifices and second cavities which communicate with the interior space between the inner and outer annular walls. The partition serves to completely separate the cavities preventing contamination of the tapped air by the injected fuel.
摘要翻译： 公开了一种用于涡轮喷气发动机的环形燃烧室的套管结构，其中空气从壳体的上游端部分抽出，同时防止这种抽吸的空气从注入的燃料中被污染。 壳体具有设置在燃烧室两侧的环形内壁和外壁。 壳体具有附接到排气涡轮机的下游端的上游端。 外部环形壳体壁限定周向间隔开的燃料喷射器孔和周向间隔开的空气攻丝孔，其与燃料喷射器孔邻接地交替。 在空气扩散器和外环形壁的内表面之间延伸的分隔壁将将扩散器和外环形壁分开的径向空间分成与空气攻丝孔和第二空腔连通的第一空腔，第一腔与第二空腔连通， 内外环形壁。 隔板用于完全分开空腔，防止被喷射的燃料污染抽空的空气。
-
公开(公告)号：US5320490A
公开(公告)日：1994-06-14
申请号：US990183
申请日：1992-12-14
CPC分类号： F01D9/042 , Y02T50/672
摘要： A casing structural arm of a turbo-engine is fixed between an external ferrule and a hub of the casing and is formed as a composite material. The arm has one leading edge, one trailing edge, one radially external edge and one radially internal edge. These four edges define the four corners of the arm and securing of the arm to the ferrule and said hub is ensured by two pairs of linking braces respectively secured to the four corners of the arm.
摘要翻译： 涡轮发动机的套管结构臂固定在壳体的外套圈和轮毂之间，并形成为复合材料。 臂具有一个前缘，一个后缘，一个径向外部边缘和一个径向内部边缘。 这四个边缘限定了臂的四个角部，并将臂固定到套圈上，并且所述轮毂由分别固定到臂的四个角的两对连接支架确保。
-
8.发明授权Sealing assembly between an aircraft fuselage and the outer nozzle flaps of a turbojet engine mounted in the rear end of the fuselage 失效涡轮机后端安装的涡轮发动机的空气喷嘴与外部喷嘴之间的密封装配
公开(公告)号：US5222692A
公开(公告)日：1993-06-29
申请号：US799961
申请日：1991-11-29
申请人： Pierre A. Glowacki
发明人： Pierre A. Glowacki
CPC分类号： F02C7/28 , F01D11/005 , F02K1/805 , Y02T50/672
摘要： An aircraft having a turbojet engine disposed within its fuselage wherein towards the rear end thereof it is provided with a sealing assembly between the rear end of the fuselage and the outer flaps of the nozzle of the turbojet engine, the sealing assembly including a central carrier ring, preferably made of a carbon-epoxy material, secured to the turbojet engine by supporting legs, a hollow front seal at the front end of the carrier ring engaging the inner surface of the fuselage, and a hollow rear seal at the rear end of the carrier ring engaging each of the outer flaps, the carrier ring also engaging the inner surface of the fuselage at a position spaced rearwardly from the front seal.
摘要翻译： 具有设置在其机身内的涡轮喷气发动机的飞行器，其中朝向其后端，在机身的后端与涡轮喷气发动机的喷嘴的外侧翼片之间设置有密封组件，该密封组件包括中央载体环 优选由碳环氧材料制成，通过支撑腿固定到涡轮喷气发动机，在承载环的前端处接合机身内表面的中空前密封件和在机身的后端处的中空后密封件 承载环接合每个外翼片，承载环还在与前密封件向后间隔开的位置处接合机身的内表面。
-
公开(公告)号：US4522562A
公开(公告)日：1985-06-11
申请号：US97741
申请日：1979-11-21
CPC分类号： B23H9/10 , F01D5/087 , F01D5/187 , Y02T50/671 , Y02T50/676
摘要： The present invention concerns the cooling of turbine rotors, especially those of aircraft turboreactors, and discloses a turbine disc equipped with two sets of channels bored respectively close to each of the sides of the disc and in conformity with its profile, in which flows the cooling air of the turbine blades in order to superficially cool the disc.
摘要翻译： 本发明涉及涡轮转子的冷却，特别是飞机涡轮反应器的涡轮转子的冷却，并且公开了一种涡轮盘，其配备有两组通道，其分别靠近盘的每个侧面并与其轮廓一致，其中冷却 涡轮叶片的空气，以便表面冷却该盘。
-
公开(公告)号：US5119625A
公开(公告)日：1992-06-09
申请号：US545643
申请日：1990-06-29
申请人： Pierre A. Glowacki
发明人： Pierre A. Glowacki
IPC分类号： F04D27/02
CPC分类号： F04D27/0215 , F04D27/023
摘要： A blow-off device for a gas turbine bypass engine having a primary air flow path separated from an outer secondary air flow path by a partition includes a plurality of discharge passages passing through the partition from the primary air flow path to the secondary air flow path, each of the discharge passages having a first hinged flap in the outer wall of the primary air flow path, a second hinged flap in the inner wall of the secondary air flow path, and a connecting rod mechanically interlinking the first and second flaps, the connecting rod being hinged at one of its end to the first flap and at its other end to the second flap.
摘要翻译： 用于具有通过分隔件与外部二次空气流动路径隔开的一次空气流动路径的燃气涡轮机旁路引擎的吹出装置包括多个排出通道，其通过隔板从一次空气流动通道流向二次空气流动路径 每个排出通道在一次空气流路的外壁中具有第一铰接翼片，在二次空气流动路径的内壁中具有第二铰接翼片，以及将机械地连接第一和第二翼片的连杆， 连杆在其一端铰接到第一挡板上，另一端铰接在第二挡板上。
-
-
-
-
-
-
-
-
-
搜索结果
14 条记录 (耗时 0.012 秒)
