公开(公告)号：WO2015175073A3

公开(公告)日：2016-01-14

申请号：PCT/US2015016584

申请日：2015-02-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GALLAGHER EDWARD J ,  MONZON BYRON R ,  LIU LING ,  LI LINDA S ,  WHITLOW DARRYL ,  FORD BARRY M

IPC: F01D5/14 ,  F04D29/38

CPC classification number: 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

Abstract: 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.

Abstract translation: 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。

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：SG11201403700YA

公开(公告)日：2014-10-30

申请号：SG11201403700Y

申请日：2012-12-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： GALLAGHER EDWARD J ,  MONZON BYRON R ,  LIU LING ,  LI LINDA S ,  WHITLOW DARRYL

IPC: F01D5/14 ,  F02K3/06

Abstract: 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 α with the axis. The stagger angle α 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.