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公开(公告)号：EP3108103A4
公开(公告)日：2017-02-22
申请号：EP14883154
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
CPC classification number: F04D29/38 , F01D5/141 , F02C3/04 , F02C7/36 , F02K3/06 , F04D29/325 , F05D2220/32 , F05D2220/36 , F05D2240/35 , Y02T50/672 , Y02T50/673
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公开(公告)号：EP2809579A4
公开(公告)日：2015-09-30
申请号：EP12871777
申请日：2012-12-28
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GALLAGHER EDWARD J , MONZON BYRON R , LIU LING , LI LINDA S , WHITLOW DARRYL
CPC classification number: F02K3/06 , F01D5/141 , F02C7/36 , Y02T50/673
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 ± with the axis. The stagger angle ± 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.
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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
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。
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公开(公告)号：EP3108123A4
公开(公告)日：2017-03-08
申请号：EP15796827
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
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。 翼型在交错角和跨度位置之间具有关系，其定义了从90％跨度到100％跨距的交错角大于32°的曲线。
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公开(公告)号：EP3108121A4
公开(公告)日：2017-03-08
申请号：EP15793323
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
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
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Patent Agency Ranking
公开(公告)号：EP3108107A4
公开(公告)日：2017-03-08
申请号：EP15751454
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: F04D29/38 , F01D5/141 , F01D17/162 , F01D25/24 , F02C3/04 , F02C7/36 , F02K3/06 , F04D29/325 , F05D2220/323 , F05D2220/36 , F05D2240/35 , F05D2260/4031 , Y02T50/672 , Y02T50/673
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公开(公告)号：EP3108122A4
公开(公告)日：2017-03-01
申请号：EP15793425
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
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
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公开(公告)号：EP3108111A4
公开(公告)日：2017-03-01
申请号：EP15752124
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
CPC classification number: F04D29/324 , F01D5/141 , F01D17/162 , F02C3/04 , F02C7/36 , F04D19/02 , F04D29/325 , F04D29/544 , F05D2220/32 , F05D2220/36 , F05D2240/121 , F05D2240/303 , 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 extending in radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a leading edge dihedral angle and span position defined by a curve with the leading edge dihedral angle including 10° or less change from 0% span to 60% span.
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沿从0％跨度位置到100％跨度位置的径向方向延伸。 翼型具有前缘二面角与由前缘二面角包括10°或更小的曲线定义的跨度位置之间的关系，所述前缘二面角从0％跨度到60％跨度变化。
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公开(公告)号：EP3108105A4
公开(公告)日：2017-12-06
申请号：EP14883503
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
CPC classification number: F01D5/141 , F02C3/04 , F02C7/36 , F04D29/324 , F05D2220/36 , F05D2240/303 , F05D2240/304 , F05D2250/38 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: An airfoil for a turbine engine 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 relationship between an axial leading edge location and a span position that is at least a third order polynomial with a generally U-shaped curve having an initial negative slope followed by a positive slope. The positive slope leans aftward and the negative slope leans forward. The curve has a critical point in the range of 30-50% span position at which the curve changes from the negative slope to the positive slope. The curve is generally linear from 55% span to 75% span and has a positive slope that increases at a rate of about 0.0875 inch (2.22 mm) per 1% span, +/−0.04 inch (1.01 mm) per 1% span.
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公开(公告)号：EP3126638A4
公开(公告)日：2017-04-12
申请号：EP15774355
申请日：2015-03-30
Applicant: UNITED TECHNOLOGIES CORP
Inventor： BILLINGS SCOTT C , GOTTSCHALK MICHAEL K , OWEN WILLIAM D , GALLAGHER EDWARD J , WHITLOW DARRYL , CHUANG SUE-LI , SADEGHI MANI
IPC: F01D5/14
CPC classification number: F04D29/384 , F01D5/141 , F02C3/04 , F02C7/36 , F02K3/06 , F05D2220/36 , F05D2240/35 , F05D2250/70 , Y02T50/672 , Y02T50/673
Abstract: In one exemplary embodiment, an airfoil for a turbine engine includes an airfoil that has pressure and suction sides and extends 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 curve that corresponds to a relationship between a leading edge dihedral and a span position. The leading edge dihedral has a portion of the curve with a change in dihedral in the range of 90% to 100% span position of greater than 10°. A positive dihedral corresponds to suction side-leaning. A negative dihedral corresponds to pressure side-leaning.
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