公开(公告)号：US08864457B2

公开(公告)日：2014-10-21

申请号：US13589264

申请日：2012-08-20

Applicant: Anthony J. Malandra ,  Ching-Pang Lee ,  Barry J. Brown ,  Eric Munoz

Inventor： Anthony J. Malandra ,  Ching-Pang Lee ,  Barry J. Brown ,  Eric Munoz

IPC: F01D25/30 ,  F01D9/04 ,  F01D5/14

CPC classification number: F01D5/141 ,  F01D9/041 ,  F05D2220/3213 ,  F05D2250/74

Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 3, 5 and 7.

Abstract translation: 一种用于安装在燃气涡轮发动机中的涡轮机翼型组件。 翼型组件包括端壁和从端壁径向向外延伸的翼型件。 翼型件包括压力和抽吸侧壁，其限定翼型的弦向间隔开的前缘和后缘。 机翼平均线被定义为位于压力和吸力侧壁之间的中心。 平均线与平行于前缘和后缘的发动机轴线的直线之间的角度限定了气流入口角α和出口角度＆bgr。 翼型件的入口角和出口角度基本上与表1,3,5和7中的一个中的入口角度值α和出口角度值bgr对成对。

公开(公告)号：US20130089415A1

公开(公告)日：2013-04-11

申请号：US13589264

申请日：2012-08-20

Applicant: Barry J. Brown ,  Ching-Pang Lee ,  Anthony J. Malandra ,  Eric Munoz

Inventor： Barry J. Brown ,  Ching-Pang Lee ,  Anthony J. Malandra ,  Eric Munoz

IPC: F01D9/04

CPC classification number: F01D5/141 ,  F01D9/041 ,  F05D2220/3213 ,  F05D2250/74

Abstract: A turbine airfoil assembly for installation in a gas turbine engine. The airfoil assembly includes an endwall and an airfoil extending radially outwardly from the endwall. The airfoil includes pressure and suction sidewalls defining chordally spaced apart leading and trailing edges of the airfoil. An airfoil mean line is defined located centrally between the pressure and suction sidewalls. An angle between the mean line and a line parallel to the engine axis at the leading and trailing edges defines gas flow entry angles, α, and exit angles, β. Airfoil inlet and exit angles are substantially in accordance with pairs of inlet angle values, α, and exit angle values, β, set forth in one of Tables 1, 3, 5 and 7.

Abstract translation: 一种用于安装在燃气涡轮发动机中的涡轮机翼型组件。 翼型组件包括端壁和从端壁径向向外延伸的翼型件。 翼型件包括压力和抽吸侧壁，其限定翼型的弦向间隔开的前缘和后缘。 机翼平均线被定义为位于压力和吸力侧壁之间的中心。 平均线与平行于前缘和后缘的发动机轴线的直线之间的角度限定了气流入口角α和出口角度＆bgr。 翼型件的入口角和出口角度基本上与表1,3,5和7中的一个中的入口角度值α和出口角度值bgr对成对。