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公开(公告)号：US10519971B2
公开(公告)日：2019-12-31
申请号：US15113868
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
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 geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. XLE corresponds to an axial distance from a leading edge to the reference point at a given span position. XTE corresponds to a axial distance from a trailing edge to the reference point at a given span position. Xd corresponds to an axial stacking offset at a given span position. (XLE−Xd)/(Xd−XTE) at 100% span position is about 1 and (XLE−Xd)/(Xd−XTE) at 90% span position is about 1.
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公开(公告)号：US09988908B2
公开(公告)日：2018-06-05
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：US09574574B2
公开(公告)日：2017-02-21
申请号：US15191860
申请日：2016-06-24
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 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.
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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公开(公告)号：US20160341212A1
公开(公告)日：2016-11-24
申请号：US15113868
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
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 geometry corresponds to axial leading and trailing edge curves and an axial stacking offset curve. The airfoil extends from a root and a zero axial reference point corresponds to axial center of the root. XLE corresponds to an axial distance from a leading edge to the reference point at a given span position. XTE corresponds to a axial distance from a trailing edge to the reference point at a given span position. Xd corresponds to an axial stacking offset at a given span position. (XLE−Xd)/(Xd−XTE) at 100% span position is about 1 and (XLE−Xd)/(Xd−XTE) at 90% span position is about 1.
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。 翼型几何对应于轴向前缘和后缘曲线以及轴向堆叠偏移曲线。 翼型从根部延伸，零轴向参考点对应于根部的轴向中心。 XLE对应于在给定跨度位置处从前缘到参考点的轴向距离。 XTE对应于在给定跨度位置处从后缘到参考点的轴向距离。 Xd对应于给定跨度位置处的轴向堆积偏移。 （XLE-Xd）/（Xd-XTE）在100％跨度位置约为1，（XLE-Xd）/（Xd-XTE）在90％跨度位置约为1。
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公开(公告)号：US20160238023A1
公开(公告)日：2016-08-18
申请号：US15063594
申请日：2016-03-08
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 constant or has a decreasing total chord length from the first peak toward 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). The curve is at least a third order polynomial and has an initial positive slope.
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，曲线或者保持恒定，或者从第一个峰到100％的跨度位置具有减小的总弦长。 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。 该曲线是至少三阶多项式并具有初始正斜率。
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Patent Agency Ranking
公开(公告)号：US09399917B2
公开(公告)日：2016-07-26
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
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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公开(公告)号：US10550852B2
公开(公告)日：2020-02-04
申请号：US15460333
申请日：2017-03-16
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: A gas turbine engine includes a combustion section arranged between a compressor section and a turbine section that extend in an axial direction. A fan section is arranged upstream from the compressor section. An airfoil is arranged in one of the fan section, the compressor section and the turbine section. The airfoil 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 has a leading edge that is projected onto a plane from various views and the plane is perpendicular to a viewing direction which corresponds to the various views. The plane is parallel with the axial direction in a 0° view. The various views include the 0° view which projects into an axial plane in the axial direction. A 90° view projects into a tangential plane in a tangential direction normal to the axial direction and views between the 0° and 90° views. The airfoil has a maximum leading edge projection in a 20° to 40° view. The radial direction is normal to the axial and tangential directions.
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公开(公告)号：US10393139B2
公开(公告)日：2019-08-27
申请号：US15113564
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
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 tangential leading edge location and a span position that corresponds to a curve that is at least a third order polynomial with a generally S-shaped curve that has an initial negative slope followed by a positive slope and then a second negative slope. The positive slope leans toward the suction side and the negative slopes lean toward the pressure side.
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公开(公告)号：US10358925B2
公开(公告)日：2019-07-23
申请号：US15294939
申请日：2016-10-17
Applicant: United Technologies Corporation
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
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 stacking offset and a span position that includes at least one positive and negative slope. The positive slope leans aftward and the negative slope leans forward relative to an engine axis. The positive slope crosses an initial axial stacking offset corresponding to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is less than 2.0.
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公开(公告)号：US20170241268A1
公开(公告)日：2017-08-24
申请号：US15113607
申请日：2014-08-22
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
Abstract: 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 has a relationship between an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/−0.04 inch (1.01 mm) per 1% span.
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