公开(公告)号：WO2015175058A3

公开(公告)日：2016-01-14

申请号：PCT/US2015016135

申请日：2015-02-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GALLAGHER EDWARD J ,  BRILLIANT LISA I ,  STRACCIA JOSEPH C ,  STEPHENS MARK A ,  BALAMUCKI STANLEY J ,  HUDON KATE

IPC: F01D5/14 ,  F04D29/38

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。

公开(公告)号：WO2015175044A3

公开(公告)日：2016-01-14

申请号：PCT/US2015015579

申请日：2015-02-12

Applicant: UNITED TECHNOLOGIES CORP

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。

公开(公告)号：WO2015175051A2

公开(公告)日：2015-11-19

申请号：PCT/US2015016018

申请日：2015-02-16

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GALLAGHER EDWARD J ,  BRILLIANT LISA I ,  STRACCIA JOSEPH C ,  BALAMUCKI STANLEY J ,  STEPHENS MARK A ,  HUDON KATE

IPC: F01D5/14 ,  F04D29/38

CPC classification number: 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

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.

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。 翼型件具有轴向堆积偏移和跨度位置之间的关系，其包括从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。

公开(公告)号：WO2015175043A3

公开(公告)日：2016-01-28

申请号：PCT/US2015015561

申请日：2015-02-12

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GALLAGHER EDWARD J ,  BRILLIANT LISA I ,  STRACCIA JOSEPH C ,  BALAMUCKI STANLEY J ,  STEPHENS MARK A ,  HUDON KATE

IPC: F01D5/14

CPC classification number: F04D29/384 ,  F01D5/141 ,  F01D9/041 ,  F02C3/04 ,  F02K3/12 ,  F04D29/324 ,  F04D29/325 ,  F04D29/544 ,  F04D29/563 ,  F05D2220/32 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2240/35 ,  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 to a 100% span position. The airfoil has a relationship between a leading edge angle and span position that defines a curve with at least one of a decreasingly negative slope or a positive slope from 80% span to 100% span.

Abstract translation: 涡轮发动机的翼型包括从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。 翼型件具有前缘角度和跨度位置之间的关系，其限定了具有从80％跨度到100％跨度的递减负斜率或正斜率中的至少一个的曲线。

公开(公告)号：WO2015178974A3

公开(公告)日：2016-01-14

申请号：PCT/US2015015575

申请日：2015-02-12

Applicant: UNITED TECHNOLOGIES CORP

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。

公开(公告)号：WO2015175056A3

公开(公告)日：2016-01-14

申请号：PCT/US2015016091

申请日：2015-02-17

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GALLAGHER EDWARD J ,  BRILLIANT LISA I ,  STRACCIA JOSEPH C ,  BALAMUCKI STANLEY J ,  STEPHENS MARK A ,  HUDON KATE

IPC: F01D5/14 ,  F04D29/38

CPC classification number: 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

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 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.

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。 翼型具有前缘扫掠角度和跨度位置之间的关系，其中前缘扫掠角度在0％跨度处为正的曲线，并在小于80％跨距的跨度位置处跨过负前缘扫掠角度。 负扫描角在向前方向，正扫掠角处于向后方向。

公开(公告)号：WO2015175052A3

公开(公告)日：2016-01-14

申请号：PCT/US2015016032

申请日：2015-02-16

Applicant: UNITED TECHNOLOGIES CORP

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。

公开(公告)号：WO2015175045A2

公开(公告)日：2015-11-19

申请号：PCT/US2015015586

申请日：2015-02-12

Applicant: UNITED TECHNOLOGIES CORP

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 ,  F02C3/04 ,  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

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.

Abstract translation: 涡轮发动机的翼型件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。 翼型在前缘角和跨度位置之间有一个关系，该距离定义了在100％跨度下前缘角小于40°的曲线。

公开(公告)号：EP3108112A4

公开(公告)日：2017-02-22

申请号：EP15752432

申请日：2015-02-17

Applicant: UNITED TECHNOLOGIES CORP

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。

公开(公告)号：EP3108108A4

公开(公告)日：2017-03-01

申请号：EP15751498

申请日：2015-02-17

Applicant: UNITED TECHNOLOGIES CORP

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 ,  F01D17/162 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D29/325 ,  F04D29/522 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/35 ,  F05D2250/71 ,  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 tangential trailing edge position and span position that defines a curve with a non-positive slope from 90% span to 100% span. The non-positive slope corresponds to a pressure side-leaning trailing edge.

Abstract translation: 具有齿轮架构的涡轮发动机的压缩机翼型包括从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。 翼型具有切向后缘位置和跨度位置之间的关系，其定义了从90％跨度到100％跨度的非正斜率的曲线。 非正斜率对应于压力侧倾后缘。