-
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。
-
公开(公告)号：US20200277870A1
公开(公告)日：2020-09-03
申请号：US16719130
申请日：2019-12-18
发明人： Shigeki SENOO , Kazuhiro MOMMA
摘要： To provide an axial flow turbine that can reduce interference loss and secondary flow loss, and can reduce mixing loss. An axial flow turbine includes: stator blades provided on the inner-circumference side of a diaphragm outer ring; a diaphragm inner ring provided on the inner-circumference side of the stator blades; moving blades provided on the outer-circumference side of a rotor; a shroud provided on the outer-circumference side of the moving blades; a main flow path constituted by a flow path formed between an inner circumferential surface of the diaphragm outer ring and an outer circumferential surface of the diaphragm inner ring, and a flow path formed between an inner circumferential surface of the shroud and an outer circumferential surface of the rotor; and a cavity formed between the diaphragm inner ring and the rotor. The outer circumferential surface of the rotor has protruding portions and depressed portions. Each depressed portion extends along a relative flow direction of a working fluid passed through the stator blades in the main flow path.
-
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.
-
公开(公告)号：US20200277869A1
公开(公告)日：2020-09-03
申请号：US16708753
申请日：2019-12-10
发明人： Shigeki SENOO , Kazuhiro MOMMA
摘要： To provide an axial flow turbine that can reduce circumferential pressure differences to reduce loss. The axial flow turbine includes: stator blades arrayed in the circumferential direction; and a diaphragm inner ring having an outer circumferential surface that interconnects the stator blades on their inner-circumference side and constitutes a wall surface of a main flow path. The outer circumferential surface of the diaphragm inner ring has depressed portions. Each depressed portion is formed in an area that is on the downstream side of a throat where the distance between a suction surface of one stator blade of a pair of adjacent blades and a pressure surface of other stator blade of the pair of adjacent blades becomes the shortest, and that lies in the circumferential direction within a range of a throat position on the suction surface of the one stator blade to a downstream edge position of the one stator blade. The area includes a downstream edge position of the outer circumferential surface in the axial direction.
-
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.
-
-
-
-
搜索结果
5 条记录 (耗时 0.014 秒)
