公开(公告)号：SG11201403867QA

公开(公告)日：2014-09-26

申请号：SG11201403867Q

申请日：2013-01-11

Applicant: UNITED TECHNOLOGIES CORP

Inventor： BALTAS CONSTANTINE ,  PRASAD DILIP ,  GALLAGHER EDWARD J

IPC: F01D5/14

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.

公开(公告)号：EP3108100A4

公开(公告)日：2017-11-22

申请号：EP14882896

申请日：2014-08-25

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F04D29/32 ,  F01D5/14 ,  F02C7/00 ,  F04D29/38

CPC classification number: F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02C7/36 ,  F04D29/324 ,  F04D29/325 ,  F04D29/386 ,  F05D2200/222 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2250/713 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil for a turbine engine includes pressure and suction sides that extend 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 tangential leading edge location and a span position that corresponds to a curve that is at least a third order polynomial with a generally S-shaped curve that has an initial negative slope followed by a positive slope and then a second negative slope. The positive slope leans toward the suction side and the negative slopes lean toward the pressure side.

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：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：EP3108109A4

公开(公告)日：2017-03-15

申请号：EP15751738

申请日：2015-02-18

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: F01D5/141 ,  F02C3/107 ,  F02K3/00 ,  F02K3/06 ,  F04D29/384 ,  F05D2200/222 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/301 ,  F05D2250/713 ,  Y02T50/672 ,  Y02T50/673

公开(公告)号：EP3108101A4

公开(公告)日：2017-03-15

申请号：EP14883036

申请日：2014-08-25

Applicant: UNITED TECHNOLOGIES CORP

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

IPC: F01D5/14 ,  F02C7/00 ,  F04D29/32 ,  F04D29/38

CPC classification number: F04D29/384 ,  F01D5/141 ,  F02C3/04 ,  F02C7/36 ,  F02K3/06 ,  F04D29/324 ,  F04D29/325 ,  F04D29/386 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2250/314 ,  Y02T50/672 ,  Y02T50/673

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。