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    • 4. 发明专利
    • AXIAL FLOW TURBINES
    • JP2002256810A
    • 2002-09-11
    • JP2001060238
    • 2001-03-05
    • TOSHIBA CORP
    • MATSUDA MINORUKAWASAKI SAKAESUGIURA MASAHITOTOMINAGA JUNICHI
    • F01D9/02F01D5/14
    • PROBLEM TO BE SOLVED: To provide a axial flow turbine that has a simple structure and reduces secondary flow loss in a turbine stage channel, loss in moving blade incidence angle, and leakage loss, thus enhancing the performance of turbine stage. SOLUTION: The axial flow turbine is so arranged that, a plurality of nozzle blades 4 are radially disposed in an array between an inner diaphragm 3 and an outer diaphragm 2, wherein the nozzle blades are so disposed that their top end sides are tilted by 5 deg.-15 deg. in the blowing out direction of the fluid, with regard to the radial line extended radially from the center of the revolution of the turbines, while the nozzle blades having an identical section in the direction of the height are twisted by 0 deg.-3 deg. within the range of 70-100% of dimensionless hight at the top end side of the nozzle blades, forming a large, minimal geometrical exit angle, sin-1 (S/T), when the throat width between the arrays of blades is made S and the pitch in circumferential direction between the arrays of blades is made T.
    • 6. 发明专利
    • AXIAL FLOW TURBINE
    • JP2000248903A
    • 2000-09-12
    • JP5182399
    • 1999-02-26
    • TOSHIBA CORP
    • MATSUDA MINORUSAKAMOTO TARO
    • F01D9/02
    • PROBLEM TO BE SOLVED: To hold down the vortex flow generated in an extended passage by forming a curved protruding part connecting the wing lines, extending from diaphragm outer and inner wheel sides toward the circumferential direction of an adjacent turbine nozzle, and setting the height from the diaphragm inner wheel side of the curved protruding part to be within a specified range. SOLUTION: A turbine nozzle 14, having an extended passage formed on a diaphragm outer wheel 17 side with a slant angle δ=5-30 deg. is fixed in both ends to diaphragm inner and outer wheels 16 and 17, and the wing line extending from each fixed position to the center of the wing back surface of the adjacent turbine nozzle 14 is formed linear. A curved protruding part at an intersection Q of the wing lines from the diaphragm inner and outer wheels 16 and 17 is formed, so that the ratio of a height W from the diaphragm inner wheel 16 side to a wing length H of the turbine nozzle is within the range of W/H=50-65%. According to this, the generation of vortex flow in the extended passage of the turbine nozzle 14 can be prevented, and the secondary flow loss on the diaphragm outer wheel 17 side of the turbine nozzle 14 can be suppressed.
    • 7. 发明专利
    • Axial flow turbine
    • 轴流涡轮
    • JPH11280406A
    • 1999-10-12
    • JP8424398
    • 1998-03-30
    • Toshiba Corp株式会社東芝
    • SUZUKI TOSHIOMATSUDA MINORU
    • F01D5/20F02C7/28
    • F01D5/225
    • PROBLEM TO BE SOLVED: To reduce a leakage rate caused by the blowing out phenomenon of a seal fin, and let flow much flow rate of a moving blade passage part in a high efficiency region by controlling the flow rate in a radial direction in a moving blade wherein the inner peripheral wall surface of an integral cover is slanted along the axial direction.
      SOLUTION: A plurality of moving blades 21 are implanted around a rotary wheel and arranged in a circumferential direction. An integral cover 22 is slanted its inner peripheral wall surface along a downstream side in axial direction. The integral cover 22 and the moving blades 21 are integrally formed with each other on the blade top part of the moving blades 21. The height of an outlet of a moving blade passage is heightened more than the height of its inlet. In such a constituted axial flow turbine of a top sloped type, a plurality of recessed and projecting surface parts or a plurality of projecting fins extending in the peripheral direction are provided on the outer peripheral surface of the integral cover 22. Furthermore, the outer circumferential diameter of each recessed surface parts and projecting surface parts or projecting fins 25 and flat parts 23, 24 is changed stepwise toward the downstream in axial direction.
      COPYRIGHT: (C)1999,JPO
    • 要解决的问题:为了减少由密封翅片的吹出现象引起的泄漏率,并且通过控制在移动中的径向方向上的流量而使高速区域中的动叶片通道部分的流量流动 叶片,其中整体盖的内周壁表面沿轴向倾斜。 解决方案:围绕转轮植入多个活动叶片21,沿圆周方向布置。 整体式盖22沿轴向的下游侧倾斜其内周壁面。 一体式盖22和活动叶片21在活动叶片21的叶片顶部上彼此一体地形成。移动叶片通道的出口的高度高于其入口的高度。 在这种构成顶倾斜型的轴流式涡轮机中,在一体式盖22的外周面上设置有沿周向延伸的多个凹凸表面部分或多个突出翅片。另外,外周 每个凹入表面部分和突出表面部分或突出翅片25和平坦部分23,24的直径沿轴向向下游逐渐改变。
    • 8. 发明专利
    • AXIAL FLOW TURBINE
    • JPH10311205A
    • 1998-11-24
    • JP12372397
    • 1997-05-14
    • TOSHIBA CORP
    • MATSUDA MINORUIMAI KENICHI
    • F01D5/20F01D11/08
    • PROBLEM TO BE SOLVED: To reduce a fluid leakage quantity in a seal fin part by forming projecting fins in plural rows in the intermediate part of flat parts formed in the outer peripheral surface tip part of an integral cover arranged in a moving blade tip part, and specifying the dimension of a clearance or the like between a projecting fin tip part and a stationary part side fin tip part. SOLUTION: The inflow side end part and the outflow side end part of a working fluid are formed in flat parts 53a and 53b on the outer peripheral surface of an integral cover 52 arranged on the tip of the moving blade 51 of the stepped passage part of an axial flow turbine, and plural projecting fins 54 are formed in its intermediate part. Here, when respective outside diametrical dimensions of the flat part 53a, the projecting fins 54 and the flat part 53b are denoted by D1 to D3 and a radial directional clearance distance between the flat part 53a and a seal fin 58 tip part in a position opposed to this is denoted by C1 and a radial directional clearance distance between the projecting fins 54 and the seal fin 58 tip part in a position opposed to these is denoted by C2 , the respective parts are set so as to satisfy the relationship of [D1