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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
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。
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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
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。
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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。
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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
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。
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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。
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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。
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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
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。
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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。
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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。
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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
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.
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