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公开(公告)号：EP3108117B1
公开(公告)日：2020-02-05
申请号：EP15793112.2
申请日：2015-02-16
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公开(公告)号：EP3108123A2
公开(公告)日：2016-12-28
申请号：EP15796827.2
申请日：2015-02-12
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC分类号： F01D5/14
CPC分类号： F01D5/148 , F01D5/141 , F01D5/147 , F01D9/041 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 32° from 90% span to 100% span.
摘要翻译： 涡轮发动机的翼型包括压力侧和吸力侧，并且在径向方向上从0％跨度位置延伸至100％跨度位置。 翼型在交错角和跨度位置之间具有关系，其定义了从90％跨度到100％跨距的交错角大于32°的曲线。
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公开(公告)号：EP3108117A2
公开(公告)日：2016-12-28
申请号：EP15793112.2
申请日：2015-02-16
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F01D9/041 , F01D25/24 , F02C3/04 , F02C7/36 , F02K3/06 , F04D29/325 , F04D29/38 , F04D29/544 , F05D2220/32 , F05D2240/35 , Y02T50/672 , Y02T50/673
摘要： A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a tangential stacking offset and span position that defines a curve that is non-linear.
摘要翻译： 具有齿轮结构的涡轮发动机的压缩机翼型包括压力面和吸力面，所述压力面和吸力面在从0％跨度位置到100％跨度位置的径向方向上延伸。 翼型在切向堆叠偏移和跨度位置之间具有关系，其定义了非线性的曲线。
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公开(公告)号：EP3108113A1
公开(公告)日：2016-12-28
申请号：EP15752593.2
申请日：2015-02-16
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
CPC分类号： F04D29/324 , F01D5/141 , F01D17/162 , F02C3/04 , F02C7/36 , F02K3/06 , F02K3/072 , F04D29/325 , F04D29/38 , F05D2220/32 , F05D2220/3217 , F05D2240/35 , F05D2250/70 , F05D2250/71 , F05D2260/40311 , Y02T50/672 , Y02T50/673
摘要： A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with a decreasing camber angle from 80% span to 100% span.
摘要翻译： 具有齿轮结构的涡轮发动机的压缩机翼型包括压力面和吸力面，所述压力面和吸力面在从0％跨度位置到100％跨度位置的径向方向上延伸。 翼型在外倾角和跨度位置之间具有关系，其定义了从80％跨度到100％跨度具有递减外倾角的曲线。
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公开(公告)号：EP3108112A1
公开(公告)日：2016-12-28
申请号：EP15752432.3
申请日：2015-02-17
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC分类号： F01D5/14
CPC分类号： F01D5/148 , F01D5/12 , F01D5/14 , F01D5/141 , F01D5/147 , F01D9/041 , Y02T50/672 , Y02T50/673
摘要： A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial leading edge position and span position that defines a curve with a negative slope from 90% span to 100% span. The negative slope corresponds to a forward leaning leading edge.
摘要翻译： 具有齿轮结构的涡轮发动机的压缩机翼型包括压力面和吸力面，所述压力面和吸力面在从0％跨度位置到100％跨度位置的径向方向上延伸。 翼型在轴向前缘位置和跨度位置之间具有关系，其定义了具有从90％跨度到100％跨度的负斜率的曲线。 负斜率对应于向前倾斜的前沿。
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公开(公告)号：EP3108107A1
公开(公告)日：2016-12-28
申请号：EP15751454.8
申请日：2015-02-12
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC分类号： F01D5/14
CPC分类号： F04D29/38 , F01D5/141 , F01D17/162 , F01D25/24 , F02C3/04 , F02C7/36 , F02K3/06 , F04D29/325 , F05D2220/323 , F05D2220/36 , F05D2240/35 , F05D2260/4031 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 35° from 0% span to at least 50% span.
摘要翻译： 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从0％跨度位置到100％跨距位置的径向方向上延伸。 翼型在交错角和跨度位置之间具有关系，其定义了从0％跨度到至少50％跨距的交错角大于35°的曲线。
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公开(公告)号：EP3108122A2
公开(公告)日：2016-12-28
申请号：EP15793425.8
申请日：2015-02-17
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
CPC分类号： F04D29/384 , F01D5/141 , F02C3/067 , F04D29/324 , F04D29/544 , F04D29/563 , F05D2220/32 , F05D2220/3217 , F05D2240/121 , F05D2240/303 , F05D2240/305 , F05D2240/306 , Y02T50/672 , Y02T50/673
摘要： A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides extending in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between leading edge sweep angle and span position defined by a curve in which the leading edge sweep angle is positive at 0% span and crosses to a negative leading edge sweep angle at a span position less than 80% span. A negative sweep angle is in the forward direction, and a positive sweep angle is in the rearward direction.
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公开(公告)号：EP3108120A2
公开(公告)日：2016-12-28
申请号：EP15793268.2
申请日：2015-02-12
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F02C3/04 , F02C7/36 , F04D19/02 , F04D29/325 , F04D29/544 , F05D2220/32 , F05D2220/3217 , F05D2240/121 , F05D2240/303 , F05D2240/35 , F05D2250/71 , F05D2260/4031 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with a leading edge angle of less than 40° at 100% span.
摘要翻译： 涡轮发动机的翼型包括压力侧和吸力侧，并且在径向方向上从0％跨度位置延伸至100％跨度位置。 翼型在前缘角度和跨度位置之间具有关系，其定义了在100％跨度处具有小于40°的前缘角度的曲线。
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公开(公告)号：EP3108116A2
公开(公告)日：2016-12-28
申请号：EP15792720.3
申请日：2015-02-12
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC分类号： F01D5/14
CPC分类号： F04D29/324 , F01D5/141 , F02C3/06 , F02C7/36 , F02K3/06 , F04D29/325 , F04D29/38 , F04D29/544 , F05D2220/3216 , F05D2220/323 , F05D2240/301 , F05D2240/35 , F05D2250/70 , F05D2250/71 , F05D2260/4031 , Y02T50/672 , Y02T50/673
摘要： An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
摘要翻译： 涡轮发动机的翼型包括压力侧和吸力侧，并且在径向方向上从0％跨度位置延伸至100％跨度位置。 翼型在外倾角和跨度位置之间具有关系，该外倾角限定了具有从0％跨度到100％跨度的正斜率的外倾角曲线。
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公开(公告)号：EP3108115A2
公开(公告)日：2016-12-28
申请号：EP15792194.1
申请日：2015-02-16
发明人： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
CPC分类号： F04D29/324 , F01D5/14 , F01D5/141 , F01D9/02 , F02C3/04 , F02C7/36 , F02K3/06 , F04D29/384 , F04D29/544 , F05D2220/32 , F05D2240/35 , F05D2250/71 , F05D2260/4031 , Y02T50/672 , Y02T50/673
摘要： A compressor airfoil of a turbine engine having a geared architecture includes pressure and suction sides that extend in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between an axial stacking offset and span position that includes a curve with a negative slope from 90% span to 100% span. The negative slope leans forward relative to an engine axis.
摘要翻译： 具有齿轮结构的涡轮发动机的压缩机翼型包括压力面和吸力面，所述压力面和吸力面在从0％跨度位置到100％跨度位置的径向方向上延伸。 翼型在轴向堆叠偏移和跨度位置之间具有关系，其包括具有从90％跨度到100％跨度的负斜率的曲线。 负斜率相对于发动机轴线向前倾斜。
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