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1. 发明授权

US08434766B2 Turbine engine seals 有权
标题翻译：涡轮发动机密封
公开(公告)号：US08434766B2
公开(公告)日：2013-05-07
申请号：US12858701
申请日：2010-08-18
申请人： Xiaoqiang Zeng , Jonathon Edward Slepski , Tao Guo , Joshy John , Sudhakar Neeli
发明人： Xiaoqiang Zeng , Jonathon Edward Slepski , Tao Guo , Joshy John , Sudhakar Neeli
IPC分类号： F16J15/447
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/232 , F16J15/441 , F16J15/4472
摘要： A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees.
摘要翻译：提供密封件以防止通过固定结构和旋转结构之间的径向间隙的轴向泄漏。径向间隙由跨越径向间隙的与外径向表面相对的内径向表面限定。密封件包括设置在内径向表面和外径向表面中的一个上的至少一个区域。至少一个第一齿和至少一个第二齿从另一个径向表面突出。第二个齿比第一个牙齿短。第一齿和第二齿中的至少一个构造成在上游以一定角度延伸。该角度限定在第一或第二齿突出的径向表面与同一牙齿的上游表面之间。该角度小于或等于约80度。

2. 发明申请

US20120043728A1 TURBINE ENGINE SEALS 有权
标题翻译：涡轮发动机密封
公开(公告)号：US20120043728A1
公开(公告)日：2012-02-23
申请号：US12858701
申请日：2010-08-18
申请人： Xiaoqiang Zeng , Jonathon Edward Slepski , Tao Guo , Joshy John , Sudhakar Neeli
发明人： Xiaoqiang Zeng , Jonathon Edward Slepski , Tao Guo , Joshy John , Sudhakar Neeli
IPC分类号： F16J15/447
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/232 , F16J15/441 , F16J15/4472
摘要： A seal is provided for preventing axial leakage through a radial gap between a stationary structure and a rotating structure. The radial gap is defined by an inner radial surface opposing an outer radial surface across the radial gap. The seal includes at least one land disposed on one of the inner radial surface and outer radial surface. At least one first tooth and at least one second tooth project from the other of the radial surfaces. The second tooth is shorter than the first tooth. At least one of the first tooth and second tooth, is configured to extend at an angle upstream. This angle is defined between a radial surface from which the first or second tooth projects and an upstream surface of the same tooth. The angle is less than or equal to about 80 degrees.
摘要翻译：提供密封件以防止通过固定结构和旋转结构之间的径向间隙的轴向泄漏。径向间隙由跨越径向间隙的与外径向表面相对的内径向表面限定。密封件包括设置在内径向表面和外径向表面中的一个上的至少一个区域。至少一个第一齿和至少一个第二齿从另一个径向表面突出。第二个齿比第一个牙齿短。第一齿和第二齿中的至少一个构造成在上游以一定角度延伸。该角度限定在第一或第二齿突出的径向表面与同一牙齿的上游表面之间。该角度小于或等于约80度。

3. 发明申请

US20120294722A1 HYBRID FLOW BLADE DESIGN 有权
标题翻译：混合流动叶片设计
公开(公告)号：US20120294722A1
公开(公告)日：2012-11-22
申请号：US13109226
申请日：2011-05-17
申请人： Xiaoqiang Zeng , Jonathon Edward Slepski
发明人： Xiaoqiang Zeng , Jonathon Edward Slepski
IPC分类号： F01D5/14
CPC分类号： F01D5/141
摘要： Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution (“s/t distribution”) across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions.
摘要翻译：根据本发明的实施例的翼型导致混合控制的流动概念，其通过在机翼的端壁区域附近产生不同于在翼型件的芯部区域处的不同涡旋概念来减少泄漏损失。具体地，公开了一种具有可变非线性喉部尺寸s的涡轮机静态喷嘴翼型，其除以节距长度t，跨越其径向长度的分布（s / t分布）。在一个实施例中，提供多个静态喷嘴翼型件，其中每个静态喷嘴翼型件构造成使得相邻的静态喷嘴翼型件之间的喉部距离靠近翼型件的毂区域比靠近翼型件的芯部区域更大，并且喉部相邻的静态喷嘴翼型件之间的距离靠近翼型件的尖端区域比靠近芯部区域更小。

4. 发明授权

US08137062B2 Turbomachine nozzle 有权
标题翻译：涡轮机喷嘴
公开(公告)号：US08137062B2
公开(公告)日：2012-03-20
申请号：US12777326
申请日：2010-05-11
申请人： Xiaoqiang Zeng , Jonathon Edward Slepski , Alexander Stein
发明人： Xiaoqiang Zeng , Jonathon Edward Slepski , Alexander Stein
IPC分类号： F01D9/04
CPC分类号： F01D5/141 , F01D9/041 , Y02T50/673 , Y10T29/49229 , Y10T29/4932 , Y10T29/49995
摘要： A turbomachine includes a housing, and a plurality of turbomachine nozzles. At least one of the plurality of turbomachine nozzles includes a body having a first surface and an opposing second surface that extend between a first end and a second end. At least one of the first and second surfaces includes a profile having an angle of between about 3° and about 8° between a first line passing through the first end and a first position located between about 28% and about 38% from the first end and a second line passing through the first position and a second position located between about 53% and about 63% from the first end, and an angle of between about 10° and about 20° between the second line and a third line passing through the second position and a third position located between about 74% and about 84% from the first end.
摘要翻译：涡轮机包括壳体和多个涡轮机喷嘴。多个涡轮机喷嘴中的至少一个包括具有在第一端和第二端之间延伸的第一表面和相对的第二表面的主体。所述第一表面和所述第二表面中的至少一个包括在通过所述第一端的第一线与位于所述第一端之间的约28％至约38％之间的第一位置之间具有约3°至约8°之间的角度的轮廓以及穿过所述第一位置的第二线和从所述第一端位于约53％至约63％之间的第二位置，以及在所述第二线和穿过所述第一端的第三线之间的约10°至约20°之间的角度第二位置和第三位置从第一端位于约74％至约84％之间。

5. 发明申请

US20110278378A1 TURBOMACHINE NOZZLE 有权
标题翻译：涡轮喷嘴
公开(公告)号：US20110278378A1
公开(公告)日：2011-11-17
申请号：US12777326
申请日：2010-05-11
申请人： Xiaoqiang Zeng , Jonathon Edward Slepski , Alexander Stein
发明人： Xiaoqiang Zeng , Jonathon Edward Slepski , Alexander Stein
IPC分类号： B05B1/00 , B23P17/00
CPC分类号： F01D5/141 , F01D9/041 , Y02T50/673 , Y10T29/49229 , Y10T29/4932 , Y10T29/49995
摘要： A turbomachine includes a housing, and a plurality of turbomachine nozzles. At least one of the plurality of turbomachine nozzles includes a body having a first surface and an opposing second surface that extend between a first end and a second end. At least one of the first and second surfaces includes a profile having an angle of between about 3° and about 8° between a first line passing through the first end and a first position located between about 28% and about 38% from the first end and a second line passing through the first position and a second position located between about 53% and about 63% from the first end, and an angle of between about 10° and about 20° between the second line and a third line passing through the second position and a third position located between about 74% and about 84% from the first end.
摘要翻译：涡轮机包括壳体和多个涡轮机喷嘴。多个涡轮机喷嘴中的至少一个包括具有在第一端和第二端之间延伸的第一表面和相对的第二表面的主体。所述第一表面和所述第二表面中的至少一个包括在通过所述第一端的第一线与位于所述第一端之间的约28％至约38％之间的第一位置之间具有约3°至约8°之间的角度的轮廓以及穿过所述第一位置的第二线和从所述第一端位于约53％至约63％之间的第二位置，以及在所述第二线和穿过所述第一端的第三线之间的约10°至约20°之间的角度第二位置和第三位置从第一端位于约74％至约84％之间。

6. 发明授权

US08777564B2 Hybrid flow blade design 有权
标题翻译：混合动力叶片设计
公开(公告)号：US08777564B2
公开(公告)日：2014-07-15
申请号：US13109226
申请日：2011-05-17
申请人： Xiaoqiang Zeng , Jonathon Edward Slepski
发明人： Xiaoqiang Zeng , Jonathon Edward Slepski
IPC分类号： F01D9/02
CPC分类号： F01D5/141
摘要： Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution (“s/t distribution”) across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions.
摘要翻译：根据本发明的实施例的翼型导致混合控制的流动概念，其通过在机翼的端壁区域附近产生不同于在翼型件的芯部区域处的不同涡旋概念来减少泄漏损失。具体地，公开了一种具有可变非线性喉部尺寸s的涡轮机静态喷嘴翼型，其除以其径向长度的节距长度t，分布（“s / t分布”）。在一个实施例中，提供多个静态喷嘴翼型件，其中每个静态喷嘴翼型件构造成使得相邻的静态喷嘴翼型件之间的喉部距离靠近翼型件的毂区域比靠近翼型件的芯部区域更大，并且喉部相邻的静态喷嘴翼型件之间的距离靠近翼型件的尖端区域比靠近芯部区域更小。

7. 发明申请

US20100329853A1 MOISTURE REMOVAL PROVISIONS FOR STEAM TURBINE 审中-公开
标题翻译：蒸汽涡轮水分去除条款
公开(公告)号：US20100329853A1
公开(公告)日：2010-12-30
申请号：US12494419
申请日：2009-06-30
申请人： Tao Guo , Xiaoyue Liu , Jonathon Edward Slepski
发明人： Tao Guo , Xiaoyue Liu , Jonathon Edward Slepski
IPC分类号： F01D25/32
CPC分类号： F01D25/32 , F01D9/065 , F05D2220/31 , F05D2260/602
摘要： Disclosed herein is a moisture removal system for a steam turbine including at least one perforated ring in an outer casing enclosing a stage of the steam turbine. The ring is configured to allow moisture to pass therethrough out of a steam path of the steam turbine.
摘要翻译：本文公开了一种用于蒸汽轮机的除湿系统，其包括在外壳中的至少一个穿孔环，其包围蒸汽轮机的阶段。环被配置为允许水分从蒸汽轮机的蒸汽路径中通过。

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