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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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2.发明申请Axial Flow Compressor, Gas Turbine Including the Same, and Stator Blade of Axial Flow Compressor 审中-公开轴流压缩机，包括其的燃气轮机和轴流压缩机的定子叶片公开(公告)号：US20170030375A1
公开(公告)日：2017-02-02
申请号：US15220451
申请日：2016-07-27
发明人： Takanori SHIBATA , Naoto OMURA , Chihiro MYOREN , Yasuo TAKAHASHI
CPC分类号： F04D29/542 , F01D5/141 , F01D5/143 , F01D5/145 , F04D19/02 , F04D29/321 , F04D29/324 , F04D29/526 , F04D29/544 , F04D29/547 , F04D29/681 , F04D29/682 , F04D29/684 , F05D2220/32 , F05D2240/12 , F05D2240/122 , F05D2240/304 , F05D2240/306 , F05D2240/80 , F05D2250/71 , F05D2250/713
摘要： An axial flow compressor includes multiple rotor blade rows configured to include multiple rotor blades and multiple stator blade rows configured to include multiple stator blades, the multiple rotor blades and the multiple stator blades being arranged in an annular channel through which a working fluid flows. A portion of at least one wall surface on an inner peripheral side and an outer peripheral side of the annular channel, the portion being at an arrangement portion where at least any one blade row of the rotor blade rows and the stator blade rows is located, has a protruding portion such that downstream side part of the portion is curved so as to further protrude to the annular channel than upstream side part of the portion. Each blade of the blade row located at the protruding portion of the wall surface is configured such that an increase rate in a wall surface direction of a blade outlet angle in a blade end portion on the side of the wall surface having the protruding portion is greater than an increase rate in the wall surface direction of a blade outlet angle in a blade height intermediate portion.
摘要翻译： 轴流式压缩机包括多个转子叶片行，其被配置为包括多个转子叶片和多个定子叶片行，其被配置为包括多个定子叶片，多个转子叶片和多个定子叶片布置在工作流体流过的环形通道中。 所述环形通道的内周侧和外周侧的至少一个壁面的一部分，所述部分位于所述转子叶片列和所述定子叶片列的至少任何一个叶片排和所述定子叶片列的至少一个叶片排的布置部分， 具有突出部分，使得该部分的下游侧部分弯曲，从而比该部分的上游侧部分进一步突出到环形通道。 位于壁表面的突出部分处的叶片列的每个叶片被构造成使得在具有突出部分的壁表面侧的叶片端部中的叶片出口角的壁表面方向上的增加速率更大 比叶片高度中间部分的叶片出口角度的壁面方向的增加率高。
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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：US20180066662A1
公开(公告)日：2018-03-08
申请号：US15559164
申请日：2016-04-11
摘要： In a gas turbine manufacturing method for manufacturing a derivative gas turbine having a different cycle from a reference gas turbine including a reference compressor, a compressor of the derivative gas turbine is designed to add at least one additional stage further on an upstream side than a last stage of the reference compressor and on a downstream side of a bleed slit of a bleed chamber of the reference compressor, the compressor of the derivative gas turbine is manufactured on the basis of the design, and the derivative gas turbine is manufactured. Consequently, it is possible to manufacture a gas turbine that can secure a surge margin of a compressor with respect to fluctuation in the composition of fuel.
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公开(公告)号：US20200271007A1
公开(公告)日：2020-08-27
申请号：US16719063
申请日：2019-12-18
发明人： Takanori SHIBATA
摘要： To provide an axial flow turbine that can eliminate a circumferential velocity component of a leakage flow effectively, and attempt to collect motive power. A shroud of the axial flow turbine includes: an annular first protruding portion protruding toward the upstream side in a rotor's axis direction; an annular second protruding portion that is positioned on the outer side in the rotor's radius direction relative to the first protruding portion, protrudes toward the upstream side in the rotor's axis direction, and is longer than the first protruding portion; a circulating-flow generating chamber formed between the first protruding portion and the second protruding portion; and guide plates positioned in the circulating-flow generating chamber. The circulating-flow generating chamber is configured to generate a circulating flow such that part of leakage flow is allowed to collide with the tip surface of the first protruding portion to be directed to the outer side in the rotor's radius direction, and thereafter collide with the inner circumferential surface of the second protruding portion to be directed to the inner side in the rotor's radius direction. The guide plates are inclined opposite the rotor's rotation direction relative to the inward direction in the rotor's radius direction.
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公开(公告)号：US20160245305A1
公开(公告)日：2016-08-25
申请号：US15046881
申请日：2016-02-18
CPC分类号： F04D29/522 , F01D5/143 , F02C3/30 , F02C7/1435 , F04D19/00 , F04D29/321 , F04D29/542 , F04D29/563 , F05D2220/32 , F05D2230/50 , F05D2230/51
摘要： An object is to reduce the compressor flow rate in comparison with the reference model while maintaining a compression ratio equivalent to that in the reference model. Annulus areas required of a compressor 38 of a derivative gas turbine 200 are determined based on a compressor flow rate and a compression ratio required of the compressor 38 of the derivative gas turbine 200. Under the condition that the annulus area of each stage of the compressor 38 becomes equal to the determined annulus area, an inner radius increment and an outer radius decrement of an initial stage 36a are determined, the inner radius increment and the outer radius decrement of each of intermediate stages 36b-36e are determined so that the inner radius increment is not more than the inner radius increment of the previous stage and the outer radius decrement is not less than the outer radius decrement of the previous stage, and the inner radius increment and the outer radius decrement of a final stage 36f are determined so that the outer radius decrement is not less than the inner radius increment. The compressor 38 is designed by updating design data of components of the reference compressor 15 that deviated from the specifications due to the determination of the inner radius increment and the outer radius decrement so that the updated design data fulfill the specifications in each of the stages 36a-36f.
摘要翻译： 目的是与参考模型相比降低压缩机流量，同时保持与参考模型中的压缩比相当的压缩比。 衍生燃气轮机200的压缩机38所需的环形区域基于压缩机流量和衍生燃气轮机200的压缩机38所需的压缩比来确定。在压缩机的各级的环空区域 38变得等于所确定的环面积，初始阶段36a的内半径增量和外半径减量被确定，每个中间级36b-36e的内半径增量和外半径减量被确定为使得内半径 增量不大于前一级的内半径增量，外半径减量不小于前一级的外半径减量，并且确定最终级36f的内半径增量和外半径减量，使得 外半径减量不小于内半径增量。 压缩机38是通过更新参考压缩机15的部件的设计数据来设计的，该设计数据由于确定了内半径增量和外半径减量而偏离规格，使得更新后的设计数据满足每个级36a中的规格 -36f。
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