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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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公开(公告)号：US20150361797A1
公开(公告)日：2015-12-17
申请号：US14837183
申请日：2015-08-27
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 , F02C3/107 , F02K3/00 , F02K3/06 , F04D29/384 , F05D2200/222 , F05D2220/323 , F05D2220/36 , F05D2240/301 , F05D2250/713 , 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 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 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.
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。 翼型件具有层叠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。 正斜坡向后倾斜，负斜坡相对于发动机轴向前倾斜。 正斜率跨过与过零位置的0％跨度位置对应的初始轴向堆积偏移。 第一轴向堆叠偏移X1从过零位置提供到曲线上的负最大值。 第二轴向堆叠偏移X2从过零点提供到曲线上的最大值。 第二轴向叠置偏移量X2 / X1的比率小于2.0。
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公开(公告)号：US20150354363A1
公开(公告)日：2015-12-10
申请号：US14624666
申请日：2015-02-18
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 , F01D15/12 , F02C3/04 , F02C3/14 , F05D2220/32 , F05D2220/36 , F05D2250/71 , 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 curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.
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。 翼型件具有对应于后缘扫掠角度和跨度位置之间的关系的曲线。 在40-70％跨度位置的范围内，后缘扫掠角度在10°至20°的范围内。 后缘扫描角度从0％跨度到至少95％跨度为正。
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公开(公告)号：US20150233252A1
公开(公告)日：2015-08-20
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：US10794192B2
公开(公告)日：2020-10-06
申请号：US16048981
申请日：2018-07-30
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 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 curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 0° to 10° in a range of 10-20% span position. The trailing edge sweep angle is in a range of the trailing edge sweep angle is positive from 0% span to at least 95% span.
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Patent Agency Ranking
公开(公告)号：US10781827B1
公开(公告)日：2020-09-22
申请号：US15872171
申请日：2018-01-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Elliott , Daniel C. Falk , Myron L. Klein , Ethan C. Drew , James H. Moffitt , Darryl Whitlow , Byron R. Monzon , Jay Thomas Abraham , William R. Graves
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 27.5-28.5 inches (699-724 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 34±10% Hz, a second mode with a frequency of 90±10% Hz, a third mode with a frequency of 178±10% Hz, a fourth mode with a frequency of 222±10% Hz, a fifth mode with a frequency of 307±10% Hz and a sixth mode with a frequency of 389±10% Hz.
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公开(公告)号：US20190063227A1
公开(公告)日：2019-02-28
申请号：US16048981
申请日：2018-07-30
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 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 curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 0° to 10° in a range of 10-20% span position. The trailing edge sweep angle is in a range of the trailing edge sweep angle is positive from 0% span to at least 95% span.
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公开(公告)号：US10036257B2
公开(公告)日：2018-07-31
申请号：US14624666
申请日：2015-02-18
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 , F01D15/12 , F02C3/04 , F02C3/14 , F05D2220/32 , F05D2220/36 , F05D2250/71 , 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 curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.
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公开(公告)号：US09777580B2
公开(公告)日：2017-10-03
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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公开(公告)号：US09599064B2
公开(公告)日：2017-03-21
申请号：US14626392
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: F04D29/384 , F01D5/141 , F02C3/04 , F02K3/06 , F04D29/325 , F04D29/388 , F05D2220/323 , F05D2220/36 , F05D2240/301 , F05D2240/303 , F05D2240/35 , F05D2300/603 , Y02T50/672 , Y02T50/673
Abstract: A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. 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 maximum chord length projection that is not in an axial view.
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