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公开(公告)号：US20180010466A1
公开(公告)日：2018-01-11
申请号：US15630439
申请日：2017-06-22
发明人： Shigeki SENOO , Hisataka FUKUSHIMA
CPC分类号： F01D5/20 , F01D5/141 , F01D5/22 , F01D5/225 , F01D5/3007 , F01D11/08 , F05D2220/31 , F05D2220/3215
摘要： A moving blade 21d is disposed in a last stage closest to a diffuser 10 among a plurality of stages of a turbine 9 including a turbine rotor 12 and a stationary body 14. The diffuser 10 is connected to an outlet side of the stationary body 14. A distal end of the moving blade 21d is opposed to a seal fin 38 provided in the stationary body 14. The moving blade 21d includes a blade section 26, a cover 27 and a guide 32 provided on a moving blade distal end face 31, which is a surface of the cover 27. The moving blade distal end face 31 extends in a rotation axis direction of the turbine rotor 12, and the guide 32 includes a guide surface 41 located on a side close to the diffuser 10 with respect to the seal fin 38 and formed to incline upward in a direction from the seal fin 38 toward the diffuser 10.
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公开(公告)号：US20180058261A1
公开(公告)日：2018-03-01
申请号：US15643500
申请日：2017-07-07
发明人： Shigeki SENOO , Hisataka FUKUSHIMA
CPC分类号： F01D25/24 , F01D1/04 , F01D5/225 , F01D9/041 , F01D11/08 , F05D2220/31 , F05D2250/312
摘要： A turbine includes a turbine rotor, a stationary body that covers the turbine rotor, and a diffuser provided on an outlet side of the stationary body. Last-stage moving blades of the turbine rotor include blade sections and covers provided at distal ends of the blade sections. The diffuser is formed such that an outer circumferential surface of an inlet section is small in diameter with respect to an inner circumferential surface of an outlet section of the stationary body and a circumferential wall section of the inlet section at least partially overlaps the covers in a radial direction when viewed from the axial direction. An annular gap space between the stationary body and the covers faces a space on an outer side of an outer circumferential surface of the diffuser when viewed from the axial direction.
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公开(公告)号：US20160369654A1
公开(公告)日：2016-12-22
申请号：US15182707
申请日：2016-06-15
发明人： Hisataka FUKUSHIMA , Takeshi KUDO , Shigeki SENOO , Hideki ONO
CPC分类号： F01D25/24 , F01D5/12 , F01D5/145 , F01D5/225 , F01D9/041 , F05D2220/30 , F05D2220/31
摘要： An axial turbine includes an upstream turbine stage that includes: a cover disposed at a distal end of an upstream bucket and opposed to an inner wall of an upstream diaphragm outer ring across a gap; and a downstream diaphragm outer ring that is disposed downstream of the upstream turbine stage and that has an inner peripheral-side end wall shaped into a flare. The inner peripheral-side end wall of the downstream diaphragm outer ring has a flare angle formed to be greater than a slant angle of an inner peripheral-side wall of the cover. In the axial turbine, the inner peripheral-side end wall of the downstream diaphragm outer ring is formed to have a meridional shape that has at least one inflection point between the upstream turbine stage and a downstream turbine stage and such that a tangent at the inflection point with respect to a steam flow direction has a positive gradient.
摘要翻译： 轴流式涡轮机包括上游涡轮级，其包括：盖，其设置在上游桶的远端并且跨越间隙与上游隔膜外环的内壁相对; 以及下游隔膜外圈，其设置在上游涡轮机台的下游，并具有成形为火炬的内周侧端壁。 下游隔膜外圈的内周侧端壁具有形成为大于盖的内周侧壁的倾斜角的张开角。 在轴向涡轮机中，下游隔膜外圈的内周侧端壁形成为具有在上游涡轮级与下游涡轮级之间具有至少一个拐点的子午形状，使得在拐点处的切线 相对于蒸汽流动方向的点具有正梯度。
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公开(公告)号：US20150132114A1
公开(公告)日：2015-05-14
申请号：US14535362
申请日：2014-11-07
IPC分类号： F01D11/08
CPC分类号： F01D11/08 , F01D5/145 , F01D5/225 , F01D17/162 , F05D2220/31 , F05D2250/411
摘要： An axial turbine includes a plurality of ribs provided in such a way as to be sandwiched between the diaphragm outer ring and the axial seal fin in the gap between the shroud and the diaphragm outer ring, the ribs being extended from the diaphragm outer ring toward the shroud in the radial direction of the rotor and in the direction of the rotation axis thereof, and a guide plate provided in such a way as to be present along the axial seal fin and a face of the diaphragm outer ring, opposed to the rotor, so as to be extended in the rotation radial direction of the rotor.
摘要翻译： 轴向涡轮机包括多个肋，所述多个肋设置成在护罩和隔膜外圈之间的间隙中夹在隔膜外圈和轴向密封翅片之间，肋从隔膜外圈向着 在转子的径向和沿其旋转轴线的方向上安装有沿轴向密封翅片设置的引导板和与转子相对的隔膜外圈的表面， 以便在转子的旋转径向方向上延伸。
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公开(公告)号：US20170016342A1
公开(公告)日：2017-01-19
申请号：US15278350
申请日：2016-09-28
CPC分类号： F01D11/08 , F01D5/225 , F01D9/041 , F05D2220/31 , F05D2240/11 , F05D2240/12 , F05D2240/30
摘要： An axial flow turbine that can enhance an effect of reducing a mixing loss is disclosed. The axial flow turbine includes a plurality of stator blades provided on the inner circumferential side of a diaphragm outer ring; a plurality of rotor blades provided on the outer circumferential side of a rotor; a shroud provided on the outer circumferential side of the plurality of rotor blades; an annular groove portion formed in the diaphragm outer ring and housing the shroud therein; a clearance passage defined between the groove portion and the shroud, into which a portion of working fluid flows from the downstream side of the stator blades in a main passage; seal fins provided in the clearance passage; a circulation flow generating chamber defined on the downstream side of the clearance passage; and a plurality of shielding plates secured to the diaphragm outer ring.
摘要翻译： 公开了一种可以增强减少混合损失的效果的轴流涡轮机。 轴流涡轮机包括设置在隔膜外圈的内周侧的多个定子叶片; 设置在转子的外周侧的多个转子叶片; 设置在所述多个转子叶片的外周侧的护罩; 形成在所述隔膜外圈中并将所述护罩容纳在其中的环形槽部; 间隙通道，限定在所述槽部和所述护罩之间，一部分工作流体从所述定子叶片的下游侧在主通道中流动; 设置在间隙通道中的密封翅片; 限定在所述间隙通道的下游侧的循环流产生室; 以及固定到隔膜外圈的多个屏蔽板。
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