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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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Patent Agency Ranking
公开(公告)号：US10781827B1
公开(公告)日：2020-09-22
申请号：US15872171
申请日：2018-01-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Elliott , Daniel C. Falk , Myron L. Klein , Ethan C. Drew , James H. Moffitt , Darryl Whitlow , Byron R. Monzon , Jay Thomas Abraham , William R. Graves
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 27.5-28.5 inches (699-724 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 34±10% Hz, a second mode with a frequency of 90±10% Hz, a third mode with a frequency of 178±10% Hz, a fourth mode with a frequency of 222±10% Hz, a fifth mode with a frequency of 307±10% Hz and a sixth mode with a frequency of 389±10% Hz.
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公开(公告)号：US10711623B1
公开(公告)日：2020-07-14
申请号：US15872196
申请日：2018-01-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Elliott , Daniel C. Falk , Myron L. Klein
Abstract: In one exemplary embodiment, a turbofan engine comprises a fan section. A core section includes a turbine section arranged fluidly downstream from the compressor section. A combustor is arranged fluidly between the compressor and turbine sections. The fan and core sections are configured to produce a thrust in a range 27,000-35,000 pounds-f (120,102-156,688 N). An airfoil is arranged in the fan section. The airfoil has first and second modes each having a frequency. The first mode has the lowest frequency, and the second mode has the second lowest frequency wherein the second mode frequency is 140 Hz or less at a redline engine speed.
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公开(公告)号：US20160230572A1
公开(公告)日：2016-08-11
申请号：US14617614
申请日：2015-02-09
Applicant: United Technologies Corporation
Inventor： Scott C. Billings , William R. Graves , Jason Elliott , David P. Houston , Ethan C. Drew
Abstract: A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.
Abstract translation: 风扇叶片的燕尾根被配置为在燃气涡轮发动机的风扇组件内操作。 燕尾根沿着燕尾根的外表面施加压缩残余应力层，防止在燃气轮机发动机运行时在燕尾根内形成裂纹。 为了进一步保护和结构地增强燕尾根，在燕尾根上设置磨损覆盖物。 磨损覆盖物可以由复合层压层组成，该复合层压层结合到燕尾榫根部的金属芯上，当燃气涡轮发动机运行时，它可以提供燕尾根的附加开裂保护。
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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：US10570755B2
公开(公告)日：2020-02-25
申请号：US14617614
申请日：2015-02-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Scott C. Billings , William R. Graves , Jason Elliott , David P. Houston , Ethan C. Drew
Abstract: A dovetail root of a fan blade configured for operation within the fan assembly of a gas turbine engine. The dovetail root is imparted with a compressive residual stress layer along the outer faces of the dovetail root preventing crack formation within the dovetail root when the gas turbine engine is in operation. To further protect and structurally enhance the dovetail root, a wear covering is disposed on the dovetail root. The wear covering may consist of a composite laminate layer that is bonded to the metallic core of the dovetail root providing additional cracking protection of the dovetail root when the gas turbine engine is in operation.
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