公开(公告)号：EP3027866A4

公开(公告)日：2017-04-26

申请号：EP14831790

申请日：2014-06-19

Applicant: UNITED TECHNOLOGIES CORP

Inventor： MERRY BRIAN D ,  SUCIU GABRIEL L ,  BRILLIANT LISA I ,  ROSE BECKY E ,  DONG YUAN ,  BALAMUCKI STANLEY J

IPC: F02C3/13

CPC classification number: F02C9/18 ,  F01D5/143 ,  F02K3/075 ,  F04D19/028 ,  F04D29/547 ,  F05D2250/314 ,  F05D2260/98 ,  Y02T50/673

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。

公开(公告)号：EP3108119A4

公开(公告)日：2017-06-14

申请号：EP15793193

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

公开(公告)号：EP3108115A4

公开(公告)日：2017-03-15

申请号：EP15792194

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。

公开(公告)号：EP3108113A4

公开(公告)日：2017-03-15

申请号：EP15752593

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 ,  F01D5/141 ,  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

公开(公告)号：EP3108117A4

公开(公告)日：2017-03-22

申请号：EP15793112

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 ,  F04D29/32

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。

公开(公告)号：EP3108102A4

公开(公告)日：2017-02-22

申请号：EP14883117

申请日：2014-08-21

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 ,  F01D9/02 ,  F02C7/057 ,  F04D29/38

CPC classification number: F01D5/141 ,  F05D2220/36 ,  Y02T50/672 ,  Y02T50/673

公开(公告)号：EP2809935A4

公开(公告)日：2015-08-26

申请号：EP13775563

申请日：2013-01-18

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BRILLIANT LISA I ,  ROSE BECKY E ,  DONG YUAN ,  BALAMUCKI STANLEY J

IPC: F02K3/02 ,  F02C9/00 ,  F02K3/00

CPC classification number: F04D29/547 ,  F02K3/04 ,  F02K3/06 ,  F04D19/028 ,  F04D25/045 ,  F04D29/321 ,  F04D29/563 ,  F04D29/682 ,  F05D2220/3217 ,  F05D2220/36 ,  F05D2260/606

公开(公告)号：EP2809929A4

公开(公告)日：2015-04-15

申请号：EP13778582

申请日：2013-01-28

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BRILLIANT LISA I ,  ROSE BECKY E ,  DONG YUAN ,  BALAMUCKI STANLEY J

IPC: F02K3/072 ,  F02C7/36

CPC classification number: F01D5/141 ,  F02C7/36 ,  F02K3/072 ,  F05D2220/36 ,  Y02T50/673

Abstract: A turbine engine includes a fan section that rotates about a longitudinal axis and a compressor section. The turbine engine also includes a fan exit stator located between the fan section and the compressor section, the fan exit stator including an airfoil. The airfoil defines an entrance angle with respect to a leading edge of the airfoil and a line parallel to the longitudinal axis, and the airfoil defines an exit angle with respect to a trailing edge of the airfoil and a line parallel to the longitudinal axis. A difference between the entrance angle and the exit angle is between about 45° and about 65°. The turbine engine also includes a turbine section, and a portion of the compressor section is driven by a portion of the turbine section.

公开(公告)号：EP3108120A4

公开(公告)日：2017-03-22

申请号：EP15793268

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 ,  F04D29/32

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。