公开(公告)号：EP2900929A1

公开(公告)日：2015-08-05

申请号：EP13838329.4

申请日：2013-03-15

Applicant: United Technologies Corporation ,  Whitehurst, Sean A. ,  McComb, Patrick James ,  Drozdenko, Lee

Inventor： WHITEHURST, Sean A. ,  MCCOMB, Patrick James ,  DROZDENKO, Lee

IPC: F01D5/30 ,  F02C7/00

Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

Abstract translation: 用于燃气涡轮发动机的风扇叶片包括限定压力侧和吸入侧的翼型件。 颈部支撑翼型并通过相反的半径与燕尾相互连接。 鸠尾榫在切点处包括与半径之一相切的支承表面。 燕尾具有燕尾宽度和垂直轴承表面高度，从切点到与颈部相对的燕尾的底部。 燕尾宽度与垂直轴承表面高度的第一比率在基本上在2.32至2.90之间的范围内。

公开(公告)号：EP2900929A4

公开(公告)日：2015-12-02

申请号：EP13838329

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORP ,  WHITEHURST SEAN A ,  MCCOMB PATRICK JAMES ,  DROZDENKO LEE

Inventor： WHITEHURST SEAN A ,  MCCOMB PATRICK JAMES ,  DROZDENKO LEE

IPC: F01D5/30 ,  F02C7/00

CPC classification number: F01D5/303 ,  F01D5/28 ,  F01D5/3007 ,  F01D5/3092 ,  F02C3/04 ,  F05D2220/36 ,  F05D2250/70 ,  F05D2270/114 ,  Y02T50/671

Abstract: A blade has an airfoil extending radially outwardly of a dovetail. The dovetail has edges that will be at circumferential sides of the blade when the blade is mounted within a rotor. A bottom surface of the dovetail will be radially inward when the rotor blade is mounted in a rotor, and is formed such that a circumferentially central portion of the bottom surface is radially thicker than are circumferential edges. A fan and a gas turbine engine are also described.

公开(公告)号：WO2014046735A1

公开(公告)日：2014-03-27

申请号：PCT/US2013/031868

申请日：2013-03-15

Applicant: UNITED TECHNOLOGIES CORPORATION ,  WHITEHURST, Sean A. ,  MCCOMB, Patrick James ,  DROZDENKO, Lee

Inventor： WHITEHURST, Sean A. ,  MCCOMB, Patrick James ,  DROZDENKO, Lee

IPC: F01D5/30 ,  F02C7/00

CPC classification number: F01D5/303 ,  F01D5/28 ,  F01D5/3007 ,  F01D5/3092 ,  F02C3/04 ,  F05D2220/36 ,  F05D2250/70 ,  F05D2270/114 ,  Y02T50/671

Abstract: A fan blade for a gas turbine engine includes an airfoil that defines a pressure and suction side. A neck supports the airfoil and interconnects to a dovetail by opposing radii. The dovetail includes a bearing surface tangent to one of the radii at a tangent point. The dovetail has a dovetail width and a vertical bearing surface height from the tangent point to a bottom of the dovetail opposite the neck. A first ratio of the dovetail width to the vertical bearing surface height is in a range of substantially between 2.32 to 2.90.

Abstract translation: 用于燃气涡轮发动机的风扇叶片包括限定压力和吸力侧的翼型件。 颈部支撑翼型，并通过相对的半径与燕尾互连。 燕尾包括在切点处与半径中的一个相切的支承表面。 燕尾榫具有燕尾宽度和垂直轴承表面高度，从切线点到燕尾榫的与颈部相对的底部。 燕尾宽度与垂直承载面高度的第一比率在2.32至2.90之间的范围内。