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公开(公告)号：EP3108104B1
公开(公告)日：2019-06-12
申请号：EP14883170.4
申请日：2014-08-25
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公开(公告)号：EP3108114A1
公开(公告)日：2016-12-28
申请号：EP15752887.8
申请日：2015-02-17
发明人： GALLAGHER, Edward J. , MONZON, Byron R. , LIU, Ling , LI, Linda S. , WHITLOW, Darryl , FORD, Barry M.
IPC分类号： F01D5/14
CPC分类号： 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
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 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).
摘要翻译： 用于涡轮发动机的翼型包括压力侧和吸力侧，所述压力侧和吸力侧沿径向方向从内部流动路径位置处的0％跨度位置延伸至翼型末端处的100％跨距位置。 翼型具有总弦长和跨度位置之间的关系，并且对应于从0％跨距位置到第一峰值具有增加的总弦长的曲线。 第一个峰出现在45-65％范围的位置范围内，曲线或者保持大致恒定或者从第一个峰到100％跨度位置的总弦长减小。 总弦长位于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：EP3108100A1
公开(公告)日：2016-12-28
申请号：EP14882896.5
申请日：2014-08-25
发明人： GALLAGHER, Edward J. , MONZON, Byron R. , LIU, Ling , LI, Linda S. , WHITLOW, Darryl , FORD, Barry M.
CPC分类号： F04D29/384 , F01D5/141 , F02C3/04 , F02C7/36 , F04D29/324 , F04D29/325 , F04D29/386 , F05D2200/222 , F05D2220/32 , F05D2220/36 , F05D2240/303 , F05D2240/304 , 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 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.
摘要翻译： 用于涡轮发动机的翼型包括压力侧和吸力侧，所述压力侧和吸力侧沿径向方向从内部流动路径位置处的0％跨度位置延伸至翼型末端处的100％跨距位置。 翼型在切向前缘位置和跨度位置之间具有关系，所述跨度位置对应于至少三阶多项式的曲线，所述三阶多项式具有大致S形的曲线，所述曲线具有初始负斜率，随后是正斜率，然后是第二 负斜率。 正斜率朝向吸力侧倾斜，而负斜率朝向压力侧倾斜。
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公开(公告)号：EP3108106A1
公开(公告)日：2016-12-28
申请号：EP14883515.0
申请日：2014-08-22
发明人： GALLAGHER, Edward J. , MONZON, Byron R. , LIU, Ling , LI, Linda S. , WHITLOW, Darryl , FORD, Barry M.
CPC分类号： 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
摘要： 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.
摘要翻译： 用于涡轮发动机的翼型件包括翼型件，该翼型件具有从径向方向从内部流动路径位置处的0％跨度位置延伸至翼型尖端处的100％跨距位置的压力侧和吸力侧。 翼型在前缘二面角和跨度位置之间具有关系。 前缘二面角从0％跨度位置到100％跨度位置为负值。 正二面角对应于吸力侧倾，负二面角对应于压力侧倾。
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公开(公告)号：EP3108105A1
公开(公告)日：2016-12-28
申请号：EP14883503.6
申请日：2014-08-22
发明人： GALLAGHER, Edward J. , MONZON, Byron R. , LIU, Ling , LI, Linda S. , WHITLOW, Darryl , FORD, Barry M.
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F02C3/04 , F02C7/36 , F04D29/324 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
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.
摘要翻译： 用于涡轮发动机的翼型件包括压力侧和吸力侧，所述压力侧和吸力侧在径向方向上从内部流动路径位置处的0％跨度位置延伸至翼型尖端处的100％跨距位置。 翼型在轴向前缘位置和跨度位置之间具有至少三阶多项式之间的关系，该三阶多项式具有大致U形的曲线，该曲线具有初始负斜率，随后是正斜率。 正斜率向后倾斜，负斜率向前倾斜。 该曲线在30-50％跨度位置处的临界点处，曲线从负斜率变为正斜率。 曲线从55％跨度到75％跨度通常是线性的，并且具有正斜率，其以每1％跨度约0.0875英寸（2.22mm），每1％跨度+/- 0.04英寸（1.01mm）的速率增加。
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6.发明公开EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 审中-公开EFFIZIENTER PROPULSOR MIT NIEDRIGEMDRUCKVERHÄLTNISFÜRGASTURBINENMOTOREN
公开(公告)号：EP3085897A1
公开(公告)日：2016-10-26
申请号：EP16166928.8
申请日：2016-04-25
CPC分类号： F01D5/282 , F02K3/06 , F05D2220/327 , F05D2300/603 , Y02T50/672
摘要： A gas turbine engine (20) includes a core flow passage, a bypass flow passage, and a propulsor (42) arranged at an inlet of the bypass flow passage and the core flow passage. The propulsor (42) includes a row (72) of propulsor blades (74). The row (72) includes no more than 20 of the propulsor blades (74). The propulsor (42) has a pressure ratio between about 1.2 and about 1.7 across the propulsor blades (74).
摘要翻译： 燃气涡轮发动机（20）包括芯流路，旁通流路和配置在旁通流路和芯流路的入口的推进器（42）。 推进器（42）包括一排（72）的推进式叶片（74）。 行（72）包括不超过20个推进刀片（74）。 推进器（42）的推压刀片（74）之间的压力比介于约1.2和约1.7之间。
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公开(公告)号：EP2809579B1
公开(公告)日：2018-08-22
申请号：EP12871777.4
申请日：2012-12-28
CPC分类号： F02K3/06 , F01D5/141 , F02C7/36 , Y02T50/673
摘要： A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the propulsor and the spool such that rotation of the spool results in rotation of the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge such that the chord forms a stagger angle ± with the axis. The stagger angle ± is less than 62° at all positions along the span, with said hub being at 0% of the span and the tip being at 100% of the span.
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公开(公告)号：EP2809579A1
公开(公告)日：2014-12-10
申请号：EP12871777.4
申请日：2012-12-28
CPC分类号： F02K3/06 , F01D5/141 , F02C7/36 , Y02T50/673
摘要： A gas turbine engine includes a spool, a turbine coupled with the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool and a gear assembly coupled between the propulsor and the spool such that rotation of the spool results in rotation of the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge such that the chord forms a stagger angle ± with the axis. The stagger angle ± is less than 62° at all positions along the span, with said hub being at 0% of the span and the tip being at 100% of the span.
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公开(公告)号：EP3098384B1
公开(公告)日：2020-05-06
申请号：EP16176856.9
申请日：2012-12-28
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公开(公告)号：EP3114321A1
公开(公告)日：2017-01-11
申请号：EP15751617.0
申请日：2015-02-17
发明人： GALLAGHER, Edward J. , MONZON, Byron R. , LIU, Ling , LI, Linda S. , WHITLOW, Darryl , FORD, Barry M.
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/02 , F01D15/12 , F02C3/04 , F02C3/14 , F05D2220/32 , F05D2220/36 , F05D2250/71 , Y02T50/672 , Y02T50/673
摘要： 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.
摘要翻译： 用于涡轮发动机的翼型件包括翼型件，该翼型件具有从径向方向从内部流动路径位置处的0％跨度位置延伸至翼型尖端处的100％跨距位置的压力侧和吸力侧。 翼型具有对应于后缘掠角和跨度位置之间的关系的曲线。 后缘扫掠角在40-70％跨度位置范围内为10°至20°。 后缘扫掠角度从0％跨度到95％跨度为正值。
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