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公开(公告)号：US20160017727A1
公开(公告)日：2016-01-21
申请号：US14773927
申请日：2014-02-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Sean A. Whitehurst , Patrick James McComb , Christopher S. McKaveney
Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.
Abstract translation: 根据本公开的示例性方面的叶片包括支撑径向外部翼型件的径向内部燕尾榫; 并且所述燕尾榫具有径向厚度，所述径向厚度在所述燕尾榫的周向中心部分上比周向相对的外边缘小。
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公开(公告)号：US20160186573A1
公开(公告)日：2016-06-30
申请号：US14934449
申请日：2015-11-06
Applicant: United Technologies Corporation
Inventor： Christopher S. McKaveney , Jason Elliott
CPC classification number: F01D5/147 , F01D5/02 , F01D5/28 , F01D5/3007 , F01D5/326 , F01D21/045 , F02K3/06 , F05D2220/32 , F05D2220/36 , F05D2230/20 , F05D2240/303 , F05D2240/80 , F05D2260/30 , F05D2300/173 , F05D2300/174 , Y02T50/671
Abstract: A turbojet fan blade adapted for securement to an engine rotor includes a titanium sheath that extends continuously over its leading edge from blade tip to blade root. The sheath provides impact protection over the leading edge of the blade, and also incorporates enhanced radial securement of the sheath to the rotor. As such, a radial lock system for the sheath is disclosed that includes a fully integrated sheath portion that extends completely over the frontal face of a fan blade dovetail, providing a radial lock of the sheath to the rotor in the event of failure of any adhesive used to attach the sheath to the leading edge. Because the sheath extends continuously from blade tip to the blade root, lightning strike protection is enhanced by avoidance of any discontinuities otherwise associated with related art sheaths that typically extend over only a flow path portion of the leading edge.
Abstract translation: 适于固定到发动机转子的涡轮喷气发动机风扇叶片包括钛护套，其从其尖端到叶片根部在其前缘上连续延伸。 护套在叶片的前缘提供冲击保护，并且还包括护套与转子的增强的径向固定。 因此，公开了一种用于护套的径向锁定系统，其包括完全集成的护套部分，其完全延伸在风扇叶片燕尾形的正面上，在任何粘合剂失效的情况下提供护套向转子的径向锁定 用于将护套连接到前缘。 因为护套从叶片尖端连续地延伸到叶片根部，所以通过避免与通常仅在前缘的流动路径部分延伸的现有技术护套相关联的任何不连续性来增强雷击保护。
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公开(公告)号：US10408068B2
公开(公告)日：2019-09-10
申请号：US14773927
申请日：2014-02-18
Applicant: United Technologies Corporation
Inventor： Sean A. Whitehurst , Patrick James McComb , Christopher S. McKaveney
Abstract: A blade according to an exemplary aspect of the present disclosure includes, among other things, a radially inner dovetail supporting a radially outer airfoil; and the dovetail having a radial thickness which is less in a circumferentially center portion of the dovetail than circumferentially opposing outer edges.
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公开(公告)号：US10287891B2
公开(公告)日：2019-05-14
申请号：US14934449
申请日：2015-11-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Christopher S. McKaveney , Jason Elliott
Abstract: A turbojet fan blade adapted for securement to an engine rotor includes a titanium sheath that extends continuously over its leading edge from blade tip to blade root. The sheath provides impact protection over the leading edge of the blade, and also incorporates enhanced radial securement of the sheath to the rotor. As such, a radial lock system for the sheath is disclosed that includes a fully integrated sheath portion that extends completely over the frontal face of a fan blade dovetail, providing a radial lock of the sheath to the rotor in the event of failure of any adhesive used to attach the sheath to the leading edge. Because the sheath extends continuously from blade tip to the blade root, lightning strike protection is enhanced by avoidance of any discontinuities otherwise associated with related art sheaths that typically extend over only a flow path portion of the leading edge.
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