公开(公告)号：US20150275757A1

公开(公告)日：2015-10-01

申请号：US14430709

申请日：2013-03-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew A. Turner ,  Keith T. Salamon ,  Barry M. Ford

IPC: F02C7/04 ,  F02C7/18 ,  B64D33/02

CPC classification number: F02C7/04 ,  B64D33/02 ,  B64D2033/0226 ,  F01D17/105 ,  F02C7/18 ,  F02K3/075 ,  F05D2240/12 ,  F05D2250/52 ,  F05D2260/606 ,  Y10T137/0536

Abstract: A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an engine axis and core engine disposed within a core nacelle for driving the fan. A bypass passage is defined between the core nacelle and an outer or fan nacelle. A duct mounted within the core nacelle defines a bleed air flow path for directing bleed air from the core engine into the bypass passage. The bleed air duct includes a plurality of airfoils disposed at a defined chord angle for directing bleed airflow into the bypass passage to minimize disruption to bypass airflow.

Abstract translation: 所公开的燃气涡轮发动机包括：风扇，包括可围绕发动机轴线旋转的多个风扇叶片和设置在用于驱动风扇的核心机舱内的核心发动机。 在核心机舱和外部或风扇机舱之间限定旁路通道。 安装在核心机舱内的管道限定了用于将排气从核心发动机引导到旁路通道中的排气流动路径。 排气管道包括以限定的弦角设置的多个翼型件，用于将排气流引导到旁路通道中以最小化对旁路气流的破坏。

公开(公告)号：US20150233251A1

公开(公告)日：2015-08-20

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。