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公开(公告)号：US20170175529A1
公开(公告)日：2017-06-22
申请号：US14973875
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Ross James Gustafson , Nicholas Alvin Hogberg
CPC classification number: F01D5/141 , F01D5/145 , F04D29/324 , F05D2220/32 , F05D2240/301 , F05D2240/304 , F05D2250/70
Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
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公开(公告)号：US20170175530A1
公开(公告)日：2017-06-22
申请号：US14973894
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Sumeet Soni , Ross James Gustafson , Rohit Chouhan , Jason Adam Neville
CPC classification number: F01D5/141 , F01D5/145 , F01D5/20 , F04D29/324 , F05D2220/32 , F05D2240/122 , F05D2240/301 , F05D2250/71 , F05D2250/74
Abstract: A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.
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公开(公告)号：US09957804B2
公开(公告)日：2018-05-01
申请号：US14973875
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Rohit Chouhan , Sumeet Soni , Ross James Gustafson , Nicholas Alvin Hogberg
CPC classification number: F01D5/141 , F01D5/145 , F04D29/324 , F05D2220/32 , F05D2240/301 , F05D2240/304 , F05D2250/70
Abstract: A turbomachine includes a plurality of blades, and each blade has an airfoil. The turbomachine includes opposing walls that define a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent blades, at which adjacent blades extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
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Patent Agency Ranking
公开(公告)号：US09957805B2
公开(公告)日：2018-05-01
申请号：US14973894
申请日：2015-12-18
Applicant: General Electric Company
Inventor： Sumeet Soni , Ross James Gustafson , Rohit Chouhan , Jason Adam Neville
CPC classification number: F01D5/141 , F01D5/145 , F01D5/20 , F04D29/324 , F05D2220/32 , F05D2240/122 , F05D2240/301 , F05D2250/71 , F05D2250/74
Abstract: A blade has an airfoil, and the blade is configured for use with a turbomachine. The airfoil has a throat distribution measured at a narrowest region in a pathway between adjacent blades, at which adjacent blades extend across the pathway between opposing walls to aerodynamically interact with fluid flow. The airfoil defines the throat distribution, and the throat distribution reduces aerodynamic loss and improves aerodynamic loading on the airfoil. The airfoil has a linear trailing edge profile.
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公开(公告)号：US20150107266A1
公开(公告)日：2015-04-23
申请号：US14061146
申请日：2013-10-23
Applicant: General Electric Company
Inventor： Ross James Gustafson , Srinivasa Govardhan Jayana , Spencer Aaron Kareff , Dipesh Dinesh Nanda
IPC: F01D5/02
CPC classification number: F01D5/02 , F01D5/141 , F05D2250/74 , Y02E20/16 , Y02T50/671 , Y02T50/673
Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.
Abstract translation: 可以使用可用于确定相邻翼型之间的喉部的特定翼型轮廓来提高涡轮机频率调节，流体动力学效率和性能。 通过根据特定轮廓对喉部进行成型，可以对端壁的总压力进行通电，提高涡轮的性能。
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公开(公告)号：US10539032B2
公开(公告)日：2020-01-21
申请号：US15372548
申请日：2016-12-08
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sumeet Soni , Rohit Chouhan , Ross James Gustafson , Matthew Peter Scoffone
IPC: F01D9/04
Abstract: A turbomachine includes a plurality of nozzles, and each nozzle has an airfoil. The turbomachine has opposing walls defining a pathway into which a fluid flow is receivable to flow through the pathway. A throat distribution is measured at a narrowest region in the pathway between adjacent nozzles, at which adjacent nozzles extend across the pathway between the opposing walls to aerodynamically interact with the fluid flow. The airfoil defines the throat distribution, and the throat distribution is defined by values set forth in Table 1, where the throat distribution values are within a +/−10% tolerance of the values set forth in Table 1. The throat distribution reduces aerodynamic loss and improves aerodynamic loading on each airfoil.
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公开(公告)号：US09347320B2
公开(公告)日：2016-05-24
申请号：US14061146
申请日：2013-10-23
Applicant: General Electric Company
Inventor： Ross James Gustafson , Srinivasa Govardhan Jayana , Spencer Aaron Kareff , Dipesh Dinesh Nanda
CPC classification number: F01D5/02 , F01D5/141 , F05D2250/74 , Y02E20/16 , Y02T50/671 , Y02T50/673
Abstract: Turbine frequency tuning, fluid dynamic efficiency, and performance can be improved using a particular airfoil profile, which can be used to determine a throat between adjacent airfoils. By shaping the throat according to the particular profile, the total pressure at an endwall can be energized, improving performance of the turbine.
Abstract translation: 可以使用可用于确定相邻翼型之间的喉部的特定翼型轮廓来提高涡轮机频率调节，流体动力学效率和性能。 通过根据特定轮廓对喉部进行成型，可以对端壁的总压力进行通电，提高涡轮的性能。
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公开(公告)号：US20160024930A1
公开(公告)日：2016-01-28
申请号：US14340059
申请日：2014-07-24
Applicant: General Electric Company
Inventor： Kelvin Rono Aaron , Craig Allen Bielek , Ross James Gustafson , Ariel Caesar Prepena Jacala , Spencer Aaron Kareff , Matthew Robert Piersall , John Franklin Ryman
IPC: F01D5/14
CPC classification number: F01D5/16 , F01D5/141 , F05D2240/305 , F05D2250/711 , F05D2260/941 , Y02T50/673
Abstract: A turbomachine airfoil includes a base portion and a blade portion extending from the base portion to a tip portion defining a radial span dimension. The blade portion includes a leading edge, a trailing edge, a pressure side and a suction side. An axial chord dimension is defined between the leading edge and the trailing edge. At least one protuberance is provided on the pressure side. The at least one protuberance extends from about 10% of the axial chord dimension to about 90% of the axial chord dimension.
Abstract translation: 涡轮机翼型包括基部和从基部延伸到限定径向跨度尺寸的尖端部的叶片部分。 叶片部分包括前缘，后缘，压力侧和吸力侧。 在前缘和后缘之间限定轴向弦的尺寸。 在压力侧设置至少一个凸起。 至少一个突起从轴向弦尺寸的约10％延伸到轴向弦尺寸的约90％。
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