公开(公告)号：US09163517B2

公开(公告)日：2015-10-20

申请号：US14625413

申请日：2015-02-18

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

IPC: F01D5/14 ,  F02K3/00

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

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 stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope crosses an initial axial stacking offset that corresponds to the 0% span position at a zero-crossing position. A first axial stacking offset X1 is provided from the zero-crossing position to a negative-most value on the curve. A second axial stacking offset X2 is provided from the zero-crossing position to a positive-most value on the curve. A ratio of the second to first axial stacking offset X2/X1 is between 1.5 and 2.0 or less than 1.4.

Abstract translation: 用于涡轮发动机的翼型包括压力和吸力侧，其在径向方向上从内部流动路径位置处的0％跨度位置延伸到翼型端部处的100％跨度位置。 翼型件具有层叠偏移和跨度位置之间的关系，其是包括至少一个正斜率和负斜率的至少三阶多项式曲线。 正斜率跨过与零交叉位置处的0％跨度位置相对应的初始轴向堆积偏移。 第一轴向堆叠偏移X1从过零位置提供到曲线上的负最大值。 第二轴向堆叠偏移X2从过零点提供到曲线上的最大值。 第二轴向叠置偏移X2 / X1之间的比率在1.5至2.0或小于1.4之间。

公开(公告)号：US20150260051A1

公开(公告)日：2015-09-17

申请号：US14433700

申请日：2013-04-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Edward J. Gallagher ,  Glen E. Potter ,  Barry M. Ford

IPC: F01D9/04 ,  F02C3/107 ,  F01D25/24 ,  F01D5/02 ,  F01D1/02

CPC classification number: F01D9/04 ,  F01D1/023 ,  F01D5/021 ,  F01D5/141 ,  F01D25/24 ,  F02C3/107 ,  F02K3/06 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/60 ,  F05D2240/12 ,  Y10T29/49323

Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.

Abstract translation: 用于燃气涡轮发动机的风扇出口导叶组件包括多个导向叶片，其具有在前缘和后缘之间延伸的压力侧和吸力侧。 叶片还包括在根部和尖端之间延伸的跨度，其交错角定义为平行于发动机旋转轴线的纵向轴线和连接前缘和后缘之间的线小于约15°的角度。

公开(公告)号：US20150233323A1

公开(公告)日：2015-08-20

申请号：US14626392

申请日：2015-02-19

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Ling Liu ,  Linda S. Li ,  Darryl Whitlow ,  Barry M. Ford

IPC: F02K3/00

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。