公开(公告)号：US09470093B2

公开(公告)日：2016-10-18

申请号：US14699322

申请日：2015-04-29

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Sue-Li Chuang

IPC: F04D29/32 ,  F01D5/14

CPC classification number: F01D5/14 ,  F01D5/141 ,  F02C3/10 ,  F04D29/32 ,  F04D29/324 ,  F04D29/325 ,  F04D29/384 ,  F05D2220/36 ,  Y02T50/672 ,  Y02T50/673

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and 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. Facing pressure and suction sides of adjacent airfoils define a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side. The width diverges without converging along the channel for at least some of the span positions.

Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的风扇部分包括限定轴线的转子轮毂和围绕转子轮毂周向间隔开的翼型阵列。 每个翼型件包括在前缘和后缘之间的压力和吸力侧面，并且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。 相邻翼型件的面对压力和吸力侧在相邻翼型件的给定跨度位置处限定具有在面向的压力和吸力侧之间的宽度的弦向方向的通道。 沿着通道的每个压力侧位置处的宽度被定义为到沿吸力侧的位置的最小距离。 宽度发散，而不会沿着通道聚集至少一些跨度位置。

公开(公告)号：US20160273547A1

公开(公告)日：2016-09-22

申请号：US15045343

申请日：2016-02-17

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Sue-Li Chuang

IPC: F04D29/38 ,  F02C3/10 ,  F04D29/32

CPC classification number: F01D5/14 ,  F01D5/141 ,  F02C3/10 ,  F04D29/32 ,  F04D29/324 ,  F04D29/325 ,  F04D29/384 ,  F05D2220/36 ,  F05D2250/70 ,  Y02T50/672 ,  Y02T50/673

Abstract: A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor hub defining an axis, and an array of airfoils circumferentially spaced about the rotor hub. Each of the airfoils include pressure and suction sides between a leading edge and a trailing edge and 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, facing pressure and suction sides of adjacent airfoils defining a channel in a chordwise direction having a width between the facing pressure and suction sides at a given span position of the adjacent airfoils. The width at each pressure side location along the channel is defined as a minimum distance to a location along the suction side, the width converging and diverging along the channel for at least some span positions.

Abstract translation: 根据本公开的示例的用于燃气涡轮发动机的风扇部分包括限定轴线的转子轮毂和围绕转子轮毂周向间隔开的翼型阵列。 每个翼型件包括在前缘和后缘之间的压力和吸力侧面，并且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顶端处的100％跨度位置，面向压力和抽吸 相邻翼型件的侧面在相邻翼型件的给定跨度位置处限定在弦向方向上的通道，该通道在面对的压力和吸力侧之间具有宽度。 沿着通道的每个压力侧位置处的宽度被定义为到沿着吸力侧的位置的最小距离，在至少一些跨度位置处，沿着通道收敛和发散的宽度。