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公开(公告)号：US20160201607A1
公开(公告)日：2016-07-14
申请号：US14695373
申请日：2015-04-24
CPC分类号： F02C7/36 , F01D5/147 , F01D5/282 , F01D15/12 , F02K1/06 , F02K3/06 , F04D29/023 , F04D29/053 , F04D29/325 , F04D29/388 , F04D29/526 , F04D29/563 , F05D2220/32 , F05D2220/327 , F05D2220/36 , F05D2260/4031 , F05D2300/603 , Y02T50/672
摘要： A gas turbine engine includes a core flow passage, a bypass flow passage, and a propulsor arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor includes a row of propulsor blades. The row includes no more than 20 of the propulsor blades. The propulsor has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades.
摘要翻译： 燃气涡轮发动机包括芯流路，旁通流路和布置在旁通流路和芯流路的入口的推进器。 推进器包括一排推进刀片。 该行包括不超过20个推进刀片。 推进器在推进刀片上的压力比介于约1.2和约1.7之间。
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公开(公告)号：US09163517B2
公开(公告)日：2015-10-20
申请号：US14625413
申请日：2015-02-18
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC分类号： F01D5/141 , F02C3/107 , F02K3/00 , F02K3/06 , F04D29/384 , F05D2200/222 , F05D2220/323 , F05D2220/36 , F05D2240/301 , F05D2250/713 , Y02T50/672 , Y02T50/673
摘要： 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 crosses an initial axial stacking offset that corresponds 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 between 1.5 and 2.0 or less than 1.4.
摘要翻译： 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。 正斜率跨过与零交叉位置处的0％跨度位置相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X2 / X1之间的比率在1.5至2.0或小于1.4之间。
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公开(公告)号：US20150233323A1
公开(公告)日：2015-08-20
申请号：US14626392
申请日：2015-02-19
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
IPC分类号： F02K3/00
CPC分类号： 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
摘要： 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.
摘要翻译： 燃气涡轮发动机包括风扇部分，压缩机部分和涡轮部分，其中之一包括翼型件。 翼型件包括从径向方向延伸的压力和吸力侧，从内部流动路径位置处的0％跨度位置到翼型端部处的100％跨度位置。 翼型具有不在轴向视图中的最大弦长突出部。
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公开(公告)号：US10422226B2
公开(公告)日：2019-09-24
申请号：US15113607
申请日：2014-08-22
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
摘要： 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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公开(公告)号：US10385866B2
公开(公告)日：2019-08-20
申请号：US15113470
申请日：2014-08-25
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
摘要： 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.
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公开(公告)号：US10370974B2
公开(公告)日：2019-08-06
申请号：US14836577
申请日：2015-08-26
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
摘要： 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.
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公开(公告)号：US10309414B2
公开(公告)日：2019-06-04
申请号：US15470462
申请日：2017-03-27
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
摘要： 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 curve that corresponds 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. 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. A negative dihedral corresponds to pressure side-leaning. The trailing edge sweep angle is positive from 0%-95% span. A positive-most trailing edge sweep angle is within the range of 10° to 20° in the range of 40-70% span position. The airfoil is a fan blade for the turbine engine.
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公开(公告)号：US10184483B2
公开(公告)日：2019-01-22
申请号：US15063594
申请日：2016-03-08
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
摘要： 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.
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公开(公告)号：US09926885B2
公开(公告)日：2018-03-27
申请号：US15709540
申请日：2017-09-20
CPC分类号： F02K3/06 , F01D17/14 , F02K1/06 , F05D2220/327 , F05D2260/4031
摘要： A gas turbine engine includes a bypass flow passage that has an inlet and defines a bypass ratio in a range of approximately 8.5 to 13.5. A fan is arranged within the bypass flow passage. A first turbine is a 5-stage turbine and is coupled with a first shaft, which is coupled with the fan. A first compressor is coupled with the first shaft and is a 3-stage compressor. A second turbine is coupled with a second shaft and is a 2-stage turbine. The fan includes a row of fan blades that extend from a hub. The row includes a number (N) of the fan blades, a solidity value (R) at tips of the fab blades, and a ratio of N/R that is from 14 to 16.
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公开(公告)号：US20170191494A1
公开(公告)日：2017-07-06
申请号：US15470462
申请日：2017-03-27
发明人： Edward J. Gallagher , Byron R. Monzon , Ling Liu , Linda S. Li , Darryl Whitlow , Barry M. Ford
CPC分类号： F04D29/325 , F01D5/141 , F02K3/06 , F04D19/002 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2220/36 , F05D2240/30 , Y02T50/672 , Y02T50/673
摘要： 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 curve that corresponds 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. 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. A negative dihedral corresponds to pressure side-leaning. The trailing edge sweep angle is positive from 0%-95% span. A positive-most trailing edge sweep angle is within the range of 10° to 20° in the range of 40-70% span position. The airfoil is a fan blade for the turbine engine.
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