公开(公告)号：EP3108114A4

公开(公告)日：2017-03-15

申请号：EP15752887

申请日：2015-02-17

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/14

CPC classification number: F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02C3/14 ,  F02C7/36 ,  F02K3/04 ,  F04D29/325 ,  F05D2220/36 ,  F05D2240/35 ,  F05D2250/71 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/4031 ,  F05D2270/3013 ,  Y02T50/672 ,  Y02T50/673

公开(公告)号：EP3108106A4

公开(公告)日：2017-03-15

申请号：EP14883515

申请日：2014-08-22

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: F01D5/141 ,  F01D5/14 ,  F01D5/145 ,  F04D29/324 ,  F04D29/325 ,  F04D29/384 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/38 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil for a turbine engine includes an airfoil having 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 relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning.

Abstract translation: 用于涡轮发动机的翼型件包括翼型件，该翼型件具有从径向方向从内部流动路径位置处的0％跨度位置延伸至翼型尖端处的100％跨距位置的压力侧和吸力侧。 翼型在前缘二面角和跨度位置之间具有关系。 前缘二面角从0％跨度位置到100％跨度位置为负值。 正二面角对应于吸力侧倾，负二面角对应于压力侧倾。

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：EP2807343A4

公开(公告)日：2015-10-07

申请号：EP13741350

申请日：2013-01-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BALTAS CONSTANTINE ,  PRASAD DILIP ,  GALLAGHER EDWARD J

IPC: F01D5/14

CPC classification number: F01D5/141 ,  F05D2240/30 ,  F05D2240/301 ,  F05D2240/304 ,  Y02T50/671 ,  Y02T50/673

Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.