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公开(公告)号：US20150354362A1
公开(公告)日：2015-12-10
申请号：US14624240
申请日：2015-02-17
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F02C3/14 , F02C7/36 , F02K3/04 , F04D29/325 , F05D2220/36 , F05D2240/35 , F05D2250/71 , F05D2250/713 , F05D2250/75 , F05D2260/4031 , F05D2270/3013 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).
Abstract translation: 用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。 翼型具有总弦长和跨度位置之间的关系，并且对应于从0％跨度位置到第一峰具有增加的总弦长的曲线。 第一个峰出现在45-65％跨度位置的范围内，并且该曲线或者保持一般恒定或具有从第一峰到100％跨度位置的总弦长减小。 总和弦长度在8.2-10.5英寸（20.8-26.7厘米）范围内的0％跨度位置。
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公开(公告)号：US09140127B2
公开(公告)日：2015-09-22
申请号：US14626167
申请日：2015-02-19
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC classification number: F01D5/141 , F01D5/02 , F02C3/107 , F02K3/00 , F05D2200/222 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/30 , F05D2240/301 , F05D2250/713 , F05D2260/40311 , Y02T50/672 , Y02T50/673
Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starting at the 0% span position is either zero or positive. The first critical point is in the range of 5-15% span.
Abstract translation: 涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型末端处的100％跨度位置。 翼型件具有切向堆积偏移和跨度位置之间的关系，其是包括至少一个正斜率和负斜率的至少三阶多项式曲线。 正斜坡倾斜到吸力侧，负斜坡朝向压力侧倾斜。 从0％跨度位置开始的初始斜率为零或正。 第一个关键点在5-15％范围内。
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公开(公告)号：US10760592B1
公开(公告)日：2020-09-01
申请号：US15869253
申请日：2018-01-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Xuedong Zhou , Jordan J. Franklin , Michael A. Weisse , Lee Drozdenko , Mouhamadou Diop , Daniel W. Yebo , Linda S. Li
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 17.2-18.2 inches (436-462 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span is in a range of 10.0-11.0 inches (255-281 mm). The airfoil element includes at least two of a first mode with a frequency of 51±10% Hz, a second mode with a frequency of 147±10% Hz, a third mode with a frequency of 267±10% Hz, a fourth mode with a frequency of 350±10% Hz, a fifth mode with a frequency of 454±10% Hz and a sixth mode with a frequency of 619±10% Hz.
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公开(公告)号：US20180016912A1
公开(公告)日：2018-01-18
申请号：US15706025
申请日：2017-09-15
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/14 , F01D5/145 , F04D29/324 , F04D29/325 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: A gas turbine engine include a combustor section arranged between a compressor section and a turbine section. A fan section has multiple fan blades. A geared architecture couples the fan section to the turbine section or compressor section. The fan blades include an airfoil that has pressure and suction sides. The airfoil extends in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.
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公开(公告)号：US20170130586A1
公开(公告)日：2017-05-11
申请号：US15418115
申请日：2017-01-27
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/14 , F01D5/145 , F04D29/324 , F04D29/325 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning. The airfoil includes at least one of a least negative dihedral in a range of 5-15% span position, a least negative dihedral in a range of 0-10% span position and a least positive trailing edge dihedral in a 40%-55% span position.
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Patent Agency Ranking
公开(公告)号：US20170023004A1
公开(公告)日：2017-01-26
申请号：US15113470
申请日：2014-08-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F02C7/36 , F02K3/06 , F04D29/324 , F04D29/325 , F04D29/386 , F05D2220/32 , F05D2220/36 , F05D2250/314 , Y02T50/672 , Y02T50/673
Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil geometry corresponds to tangential leading and trailing edge curves and a tangential stacking offset curve. The airfoil extends from a root. A zero tangential reference point corresponds to tangential center of the root. YLE corresponds to a tangential distance from a leading edge to the reference point at a given span position. YTE corresponds to a tangential distance from a trailing edge to the reference point at a given span position. Yd corresponds to a tangential stacking offset at a given span position. (YLE−Yd)/(Yd−YTE) at 40% span position is about 1.5 and (YLE−Yd)/(Yd−YTE) at 20% span position is about 2.
Abstract translation: 在一个示例性实施例中，用于涡轮发动机的翼型件包括沿径向从在内部流动路径位置处的0％跨度位置延伸到在翼型末端处的100％跨度位置的压力和吸力侧。 翼型几何对应于切向前缘和后缘曲线以及切向堆积偏移曲线。 翼型从根部延伸。 零切向参考点对应于根的切线中心。 YLE对应于在给定跨度位置处从前缘到参考点的切向距离。 YTE对应于在给定跨度位置处从后缘到参考点的切线距离。 Yd对应于给定跨度位置处的切向堆积偏移。 （YLE-YD）/（YD-YTE）在40％跨度位置约为1.5，（YLE-Yd）/（Yd-YTE）在20％跨度位置约为2。
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公开(公告)号：US20160341071A1
公开(公告)日：2016-11-24
申请号：US15113310
申请日：2014-12-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Andrew G. Alarcon , Royce E. Tatton , Barry M. Ford , Linda S. Li , Matthew A. Turner
CPC classification number: F01D25/005 , B29C70/12 , B29D99/0025 , B29K2105/12 , F01D11/008 , F02K3/06 , F04D29/325 , F05D2220/36 , F05D2240/30 , F05D2240/80 , F05D2300/123 , F05D2300/2102 , F05D2300/224 , F05D2300/434 , F05D2300/436 , F05D2300/603 , Y02T50/672
Abstract: The present disclosure relates generally to the field of fan blade platforms for gas turbine engines. More specifically, the present disclosure relates to a compressed chopped fiber fan blade platform for a gas turbine engine.
Abstract translation: 本公开一般涉及用于燃气涡轮发动机的风扇叶片平台领域。 更具体地，本公开涉及一种用于燃气涡轮发动机的压缩的短切纤维风扇叶片平台。
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公开(公告)号：US09353628B2
公开(公告)日：2016-05-31
申请号：US14624025
申请日：2015-02-17
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC classification number: F01D5/141 , F01D5/14 , F01D5/145 , F04D29/324 , F04D29/325 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.
Abstract translation: 用于涡轮发动机的翼型件包括具有压力和吸力侧的翼型件，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。 翼型件具有前缘二面体和跨度位置之间的关系。 前缘二面体从0％跨度位置到100％跨度位置为负。 正二面对应于吸力侧倾，负二面对应于压力侧倾。
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公开(公告)号：US20160032728A1
公开(公告)日：2016-02-04
申请号：US14836577
申请日：2015-08-26
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC classification number: F01D5/141 , F01D5/02 , F02C3/107 , F02K3/00 , F05D2200/222 , F05D2220/32 , F05D2220/323 , F05D2220/36 , F05D2240/30 , F05D2240/301 , F05D2250/713 , F05D2260/40311 , Y02T50/672 , Y02T50/673
Abstract: An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span.
Abstract translation: 涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型末端处的100％跨度位置。 翼型件具有切向堆积偏移和跨度位置之间的关系，其是包括至少一个正斜率和负斜率的至少三阶多项式曲线。 正斜坡倾斜到吸力侧，负斜坡朝向压力侧倾斜。 在0％跨度位置开始的初始斜率为零或正。 第一个关键点是小于15％的跨度。
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公开(公告)号：US20160024929A1
公开(公告)日：2016-01-28
申请号：US14876995
申请日：2015-10-07
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC: F01D5/14
CPC classification number: F01D5/141 , F01D5/14 , F01D5/145 , F04D29/324 , F04D29/325 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil is a fan blade for a gas turbine engine. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.
Abstract translation: 用于涡轮发动机的翼型件包括具有压力和吸力侧的翼型件，所述翼型件在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型顶端处的100％跨度位置。 翼型件具有前缘二面体和跨度位置之间的关系。 前缘二面体从0％跨度位置到100％跨度位置为负。 正二面对应于吸力侧倾，负二面对应于压力侧倾。 翼型件是用于燃气轮机的风扇叶片。 翼型件具有后缘二面体和跨度位置之间的关系。 后缘二面体从0％跨度位置到100％跨度位置为正。 正二面对应于吸力侧倾，负二面对应于压力侧倾。
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