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公开(公告)号：WO2015126774A1
公开(公告)日：2015-08-27
申请号：PCT/US2015/016011
申请日：2015-02-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
CPC classification number: 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
Abstract: 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.
Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼片包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。 机翼具有外倾角和跨度位置之间的关系，其定义了从80％跨度到100％跨度的减小的外倾角的曲线。
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公开(公告)号：WO2015175052A2
公开(公告)日：2015-11-19
申请号：PCT/US2015/016032
申请日：2015-02-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC: F01D5/14
CPC classification number: 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
Abstract: 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.
Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼片包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。 翼型在定义非线性曲线的切向堆积偏移和跨度位置之间具有关系。
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公开(公告)号：WO2015126448A1
公开(公告)日：2015-08-27
申请号：PCT/US2014/052080
申请日：2014-08-21
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , STEPHENS, Mark A. , BALAMUCKI, Stanley J. , HUDON, Kate
CPC classification number: F01D5/141 , F05D2220/36 , Y02T50/672 , Y02T50/673
Abstract: An airfoil of a turbine engine includes, pressure and suction sides extending in a radial direction from a 0% span to a 100% span position. The airfoil has a relationship between a gap/chord ratio and span position that defines a curve with a gap/chord ratio of less than 0.80 from 80% span to 100% span.
Abstract translation: 涡轮发动机的翼型包括从0％跨度到100％跨度位置沿径向延伸的压力和吸力侧。 翼型具有间隙/弦比和跨度位置之间的关系，其定义了从80％跨度到100％跨度的间隙/弦比小于0.80的曲线。
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公开(公告)号：WO2015175044A2
公开(公告)日：2015-11-19
申请号：PCT/US2015/015579
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC: F01D5/14
CPC classification number: 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
Abstract: 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.
Abstract translation: 涡轮发动机的翼型包括压力和吸力侧，并且在径向方向上从0％跨度位置延伸到100％跨度位置。 翼型件具有外倾角和跨度位置之间的关系，其定义了具有从0％跨度到100％跨度的正斜率的外倾角的曲线。
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公开(公告)号：WO2015126798A1
公开(公告)日：2015-08-27
申请号：PCT/US2015/016086
申请日：2015-02-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
CPC classification number: F04D29/324 , F01D5/141 , F01D17/162 , F02C3/04 , F02C7/36 , F04D19/02 , F04D29/325 , F04D29/544 , F05D2220/32 , F05D2220/36 , F05D2240/121 , F05D2240/303 , F05D2240/35 , F05D2250/71 , F05D2260/4031 , Y02T50/672 , Y02T50/673
Abstract: 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 a leading edge dihedral angle and span position defined by a curve with the leading edge dihedral angle including 10° or less change from 0% span to 60% span.
Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼片包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。 翼型具有前缘二面角和跨度位置之间的关系，其由前缘二面角的曲线限定，包括从0％跨度到60％跨度的10°或更小的变化。
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Patent Agency Ranking
公开(公告)号：WO2015178974A2
公开(公告)日：2015-11-26
申请号：PCT/US2015/015575
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC: F01D5/14
CPC classification number: F01D5/148 , F01D5/141 , F01D5/147 , F01D9/041 , Y02T50/672 , Y02T50/673
Abstract: 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.
Abstract translation: 涡轮发动机的翼型包括压力和吸力侧，并且在径向方向上从0％跨度位置延伸到100％跨度位置。 翼型在交错角度和跨度位置之间有一个关系，该关系定义了一个交错角度曲线，该曲线大于32°，从90％跨度到100％跨度。
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公开(公告)号：WO2015175045A3
公开(公告)日：2015-11-19
申请号：PCT/US2015/015586
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC: F01D5/14
Abstract: 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.
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公开(公告)号：WO2015126793A1
公开(公告)日：2015-08-27
申请号：PCT/US2015/016078
申请日：2015-02-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
IPC: F01D5/14
CPC classification number: F01D5/148 , F01D5/12 , F01D5/14 , F01D5/141 , F01D5/147 , F01D9/041 , Y02T50/672 , Y02T50/673
Abstract: 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.
Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼片包括从0％跨度位置到100％跨度位置沿径向方向延伸的压力和吸力侧。 翼型件具有轴向前缘位置和跨度位置之间的关系，其定义了从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缘。
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公开(公告)号：WO2015175058A2
公开(公告)日：2015-11-19
申请号：PCT/US2015/016135
申请日：2015-02-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , STEPHENS, Mark A. , BALAMUCKI, Stanley J. , HUDON, Kate
CPC classification number: F04D29/544 , F01D5/141 , F02C7/36 , F02K3/072 , F04D29/324 , F05D2220/323 , F05D2240/122 , F05D2240/304 , F05D2260/40311 , Y02T50/672 , Y02T50/673
Abstract: A compressor airfoil of a turbine engine having a geared architecture 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 trailing edge angle and span position that defines a curve with a non-negative slope from 0% span to 20% span corresponding to a non-decreasing trailing edge angle.
Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼型包括压力和吸力侧面，并且在径向方向上从0％跨度位置延伸到100％跨度位置。 翼型件具有后缘角度和跨度位置之间的关系，其限定了对应于不减小的后缘角度的0％跨度至20％跨度的非负斜率的曲线。
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公开(公告)号：WO2015175051A3
公开(公告)日：2015-11-19
申请号：PCT/US2015/016018
申请日：2015-02-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GALLAGHER, Edward J. , BRILLIANT, Lisa I. , STRACCIA, Joseph C. , BALAMUCKI, Stanley J. , STEPHENS, Mark A. , HUDON, Kate
Abstract: 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.
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