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    • 51. 发明申请
    • Device for cooling turbine disks
    • 涡轮盘冷却装置
    • US20040161334A1
    • 2004-08-19
    • US10777663
    • 2004-02-13
    • SNECMA MOTEURS
    • Sebastien ImbourgJean-Luc SoupizonPhilippe Pabion
    • F01D005/14
    • F01D5/082
    • A cooling device for cooling disks of high-pressure and low-pressure turbines of a turbomachine, said device being fed with cooling air from at least one air orifice formed through a bottom annular platform for supporting at least one fixed vane of said low-pressure turbine and being disposed between an upstream flange and a downstream flange of said bottom platform, the device comprising: an upstream annular plate extending radially from the upstream flange of said bottom platform; a downstream annular plate extending radially from the downstream flange of the bottom platform, said upstream and downstream plates longitudinally defining at least one annular cavity for cooling air; a sealing device extending longitudinally between said upstream and downstream plates so as to close the cooling air cavity in leaktight manner; holding means for holding said upstream and downstream plates against the upstream and downstream flanges of said bottom platform; and a plurality of holes for injecting cooling air towards the turbine disks.
    • 一种用于冷却涡轮机的高压和低压涡轮机的盘的冷却装置,所述装置被供给来自至少一个通过底部环形平台形成的空气孔的冷却空气,用于支撑至少一个所述低压固定叶片 涡轮机并且设置在所述底部平台的上游凸缘和下游凸缘之间,所述装置包括:从所述底部平台的上游凸缘径向延伸的上游环形板; 从底部平台的下游凸缘径向延伸的下游环形板,所述上游板和下游板纵向限定至少一个用于冷却空气的环形空腔; 密封装置,其在所述上游板和下游板之间纵向延伸,以便以密封方式封闭冷却空气腔; 用于将所述上游和下游板保持抵靠所述底部平台的上游和下游凸缘的保持装置; 以及用于向涡轮盘注入冷却空气的多个孔。
    • 54. 发明申请
    • Oil-damped rolling bearing
    • 油润滑滚动轴承
    • US20040062460A1
    • 2004-04-01
    • US10671742
    • 2003-09-29
    • SNECMA MOTEURS
    • Guy Dusserre-TelmonDaniel Plona
    • F16C019/00
    • F16C33/6677F01D25/164F01D25/18F05D2240/54F16C19/26F16C19/55F16C27/045F16C2360/23
    • A rolling bearing for a turbomachine supporting a first shaft to rotate relative to a second shaft, and comprising: a plurality of rolling elements engaged between an inner annular ring mounted on the second shaft and an outer annular ring mounted on the first shaft; an oil film formed at an annular contact surface between said outer ring and said first shaft; at least one duct passing through said inner ring and opening out in an inner race for said rolling elements in order to lubricate them; and at least one additional duct passing through said inner ring and opening out outside the inner race in order to feed oil through said outer ring to said oil film under the effect of the centrifugal force generated by said second shaft rotating, said outer ring having an annular shoulder projecting radially towards the inside of said annular space, said shoulder having at least one channel opening out substantially in register with said additional duct and opening out into said oil film.
    • 一种用于涡轮机的滚动轴承,其支撑第一轴相对于第二轴旋转,并且包括:多个滚动元件,其接合在安装在所述第二轴上的内环形圈和安装在所述第一轴上的外环形圈之间; 形成在所述外圈和所述第一轴之间的环形接触表面处的油膜; 至少一个管道穿过所述内环并在用于所述滚动元件的内圈中打开,以便润滑它们; 以及至少一个通过所述内圈并且在所述内圈外部打开的附加管道,以便在由所述第二轴旋转产生的离心力的作用下将油通过所述外环供给到所述油膜,所述外圈具有 环形肩部朝向所述环形空间的内部径向突出,所述肩部具有至少一个通道,所述至少一个通道基本上与所述附加管道对齐并且打开到所述油膜中。
    • 55. 发明申请
    • Method and system for detecting damage to the rotor of an aircraft engine
    • 用于检测飞机发动机转子损坏的方法和系统
    • US20040060347A1
    • 2004-04-01
    • US10445935
    • 2003-05-28
    • SNECMA MOTEURSSNECMA SERVICES
    • Patrick ComperatPhilippe Even
    • G01M001/00
    • G01H1/006F01D21/045F01D25/04G01M15/12G01M15/14
    • The invention relates to detecting damage to the rotor of an aircraft engine that includes means for measuring vibration and speed in order to acquire data relating to the speed of the rotor and also to the amplitude and the phase of rotor vibration during a determined flight. The method comprises the following steps: reading said acquired data; calculating a mean vibration vector over a determined rotor speed range on the basis of said acquired data; calculating a vector difference between the mean vibration vector of said determined flight and the mean vibration vector of a reference flight for said rotor speed range; comparing the modulus of said vector difference with a predetermined threshold value; and issuing a warning signal when the modulus of said vector difference exceeds said predetermined threshold value, said steps being performed after said determined flight has been completed.
    • 本发明涉及检测飞机发动机的转子的损坏,其包括用于测量振动和速度的装置,以便获得与转子速度有关的数据,以及在确定的飞行期间转子振动的振幅和相位。 该方法包括以下步骤:读取所述获取的数据; 基于所述获取的数据计算确定的转子速度范围上的平均振动矢量; 计算所述确定的飞行的平均振动矢量与所述转子速度范围的参考飞行的平均振动矢量之间的矢量差; 将所述矢量差的模量与预定阈值进行比较; 以及当所述矢量差的模量超过所述预定阈值时发出警告信号,所述步骤在所述确定的飞行完成之后执行。
    • 56. 发明申请
    • Oil-damped sealed rolling bearing
    • 油润滑密封滚动轴承
    • US20040022463A1
    • 2004-02-05
    • US10462639
    • 2003-06-17
    • SNECMA MOTEURS
    • Guy Dusserre-TelmonDaniel Plona
    • F16C027/00
    • F16C33/6685F16C19/06F16C19/26F16C27/045F16C33/6659F16C2360/23
    • A rolling bearing for supporting a shaft in rotation inside an annular structural piece, said bearing defining a separation between an oil enclosure and an air enclosure, and comprising: a plurality of rolling elements engaged between an inner bearing ring and an outer bearing ring and defining a first side opening beside said air enclosure and a second side opening beside said oil enclosure; at least one annular junction piece mechanically connected to said outer bearing ring and having an annular contact surface with said structural piece; an oil film disposed at said annular contact surface between said structural piece and said junction piece and laterally defined by at least two sealing rings; sealing means covering at least part of said first side opening beside said air enclosure; first oil circulation means for feeding said oil film with oil and for feeding said rolling elements beside said oil enclosure with oil from said oil film in order to lubricate them; and second oil circulation means, independent of the first, for recovering the oil that has been used for lubricating said rolling elements, said second oil circulation means being arranged in such a manner as to avoid oil flowing towards said air enclosure.
    • 一种滚动轴承,用于在环形结构件内旋转轴支撑轴,所述轴承限定油封壳和空气外壳之间的分隔,并且包括:多个滚动元件,其接合在内轴承环和外轴承环之间并且限定 位于所述空气外壳旁边的第一侧开口和位于所述油封的旁边的第二侧开口; 至少一个环形连接件机械地连接到所述外轴承环并具有与所述结构件的环形接触表面; 油膜,设置在所述结构件和所述接合件之间的所述环形接触表面处,并由至少两个密封环横向限定; 密封装置,其覆盖所述空气外壳旁边的所述第一侧开口的至少一部分; 第一油循环装置,用于将所述油膜供给油并将所述滚动元件从所述油膜供给油,以便将所述滚动元件从所述油膜供给油以便润滑它们; 以及第二油循环装置,与第一油循环装置无关,用于回收用于润滑所述滚动元件的油,所述第二油循环装置以避免油流向所述空气箱的方式布置。
    • 60. 发明申请
    • Device for supporting and recentering the shaft of a turbojet fan after uncoupling
    • 拆卸后支撑和重新安装涡轮喷气风扇的轴的装置
    • US20030182926A1
    • 2003-10-02
    • US10387392
    • 2003-03-14
    • SNECMA MOTEURS
    • Daniel PlonaPatrick Morel
    • F02C007/20
    • F01D21/045F01D25/16F05B2260/3011F05D2260/30F16C19/52F16C2360/23
    • The invention provides a device for supporting and recentering a shaft (2) after decoupling. The device comprises an annular support (4) surrounding the shaft (2), a bearing (5) secured to the annular support (4) and having an inner ring (9) which is spaced apart from the shaft by clearance J. The inner ring (9) has two webs or tenons (14a, 14b) that are normally held to the periphery of two troughs (16a, 16b) carried by the shaft (2). Two sets of balls (28a, 28b) normally bear against the bottoms of indentations (25, 26) formed facing one another in the adjacent radial walls of the troughs (16a, 16b) and of the inner ring (9). Resilient means (26) tend to urge the troughs (16a and 16b) towards each other. In the event of the webs or tenons (14a, 14b) breaking due to a large unbalance, the balls (28a, 28b) roll on the walls of the indentations (25, 26) and move the troughs (16a, 16b) apart from each other. The resilient mans (20) tend to bring the balls (28a, 28b) back towards the bottoms of the indentations and to recenter the shaft (2) relative to the inner ring (9).
    • 本发明提供一种用于在解耦之后支撑和重新调节轴(2)的装置。 该装置包括围绕轴(2)的环形支撑件(4),固定到环形支撑件(4)并具有内部环(9)的轴承(5),该内圈与轴间隔开。 环(9)具有通常保持在由轴(2)承载的两个槽(16a,16b)的周边的两个腹板或榫头(14a,14b)。 两组球(28a,28b)通常抵靠在槽(16a,16b)和内圈(9)的相邻径向壁中彼此面对形成的凹陷(25,26)的底部。 弹性装置(26)趋向于朝向彼此推动槽(16a和16b)。 在由于大的不平衡导致腹板或榫头(14a,14b)断裂的情况下,滚珠(28a,28b)在压痕(25,26)的壁上滚动并使槽(16a,16b)从 彼此。 弹性杆(20)倾向于将球(28a,28b)返回到凹陷的底部并且相对于内圈(9)更换轴(2)。