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公开(公告)号：US09828864B2
公开(公告)日：2017-11-28
申请号：US14429029
申请日：2013-03-15
Applicant: United Technologies Corporation , Sean A. Whitehurst , Patrick James McComb , Lee Drozdenko
Inventor： Sean A. Whitehurst , Patrick James McComb , Lee Drozdenko
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.
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公开(公告)号：US20140169975A1
公开(公告)日：2014-06-19
申请号：US13718719
申请日：2012-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee Drozdenko , William R. Graves
IPC: F01D5/30
CPC classification number: F01D5/3007 , F01D5/3092 , F01D21/045
Abstract: A rotor assembly is provided that includes a rotor disk, a rotor blade and a root spacer. The rotor disk includes a slot. The rotor blade includes a blade root that is arranged within the slot. The root spacer is arranged within the slot between the rotor disk and the blade root. The root spacer includes a base segment, a side segment and a fracture feature. The base segment radially engages the rotor disk. The side segment is radially separated from the rotor disk by a gap. The fracture feature may radially fracture the root spacer at an intersection between the base segment and the side segment.
Abstract translation: 提供了一种转子组件，其包括转子盘，转子叶片和根间隔件。 转子盘包括槽。 转子叶片包括布置在槽内的叶片根部。 根间隔件布置在转子盘和叶片根部之间的槽内。 根间隔件包括基部段，侧段和断裂特征。 基座部分径向接合转子盘。 侧段通过间隙与转子盘径向分开。 断裂特征可以在基部段和侧部段之间的交叉处径向地破坏根部间隔物。
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公开(公告)号：US10087948B2
公开(公告)日：2018-10-02
申请号：US14673287
申请日：2015-03-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee Drozdenko , James O. Hansen , Christopher J. Hertel , Steven T. Holland
IPC: F01D5/30 , F04D29/34 , B05D1/02 , B05D1/18 , B29C65/66 , F04D19/00 , F04D29/02 , F04D29/38 , B29K63/00 , B29K105/06 , B29L31/08
Abstract: A fan blade and method of covering a fan blade root portion for a gas turbine engine are disclosed. The fan blade includes an airfoil having a leading edge end and a trailing edge end, a root portion having a first side surface extending from the leading edge end to the trailing edge end and a second side surface at an opposite side of the first side surface and extending from the leading edge end to the trailing edge end, and a covering disposed against the first side surface and the second side surface, wherein the covering is positioned against the root portion as a single member.
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公开(公告)号：US20160290356A1
公开(公告)日：2016-10-06
申请号：US14673287
申请日：2015-03-30
Applicant: United Technologies Corporation
Inventor： Lee Drozdenko , James O. Hansen , Christopher J. Hertel , Steven T. Holland
CPC classification number: F04D29/34 , B05D1/02 , B05D1/18 , B29C65/66 , B29K2063/00 , B29K2105/06 , B29L2031/082 , F01D5/3092 , F04D19/002 , F04D29/023 , F04D29/388 , F05D2220/36
Abstract: A fan blade and method of covering a fan blade root portion for a gas turbine engine are disclosed. The fan blade includes an airfoil having a leading edge end and a trailing edge end, a root portion having a first side surface extending from the leading edge end to the trailing edge end and a second side surface at an opposite side of the first side surface and extending from the leading edge end to the trailing edge end, and a covering disposed against the first side surface and the second side surface, wherein the covering is positioned against the root portion as a single member.
Abstract translation: 公开了一种风扇叶片和覆盖燃气轮机的风扇叶片根部的方法。 风扇叶片包括具有前缘端部和后缘端部的翼型件，根部部分具有从前缘端部延伸到后缘端部的第一侧表面和在第一侧表面的相对侧的第二侧表面 并且从所述前缘端延伸到所述后缘端部，以及覆盖物，其抵靠所述第一侧表面和所述第二侧表面设置，其中所述覆盖物作为单个构件抵靠所述根部部分定位。
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公开(公告)号：US20140219808A1
公开(公告)日：2014-08-07
申请号：US13632288
申请日：2012-10-01
Applicant: United Technologies Corporation
Inventor： Lee Drozdenko , Patrick James McComb , William R. Graves
IPC: F01D5/14
CPC classification number: F01D5/147 , F01D5/14 , F01D5/141 , F01D5/145 , F04D29/324 , F05D2220/327 , F05D2220/36 , F05D2240/303 , Y02T50/672 , Y02T50/673 , Y10T29/49336
Abstract: A sheath for a fan airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side includes a solid portion to wrap around the airfoil leading edge; a first wing attached to the suction side of the airfoil; and a second wing attached to the pressure side of the airfoil. At least one of the first wing and the second wing extends at least about 35% of the chord of the airfoil.
Abstract translation: 一种风扇翼型的护套，其具有沿翼弦方向的前缘和后缘，翼展方向上的尖端和根部，吸力侧和压力侧包括围绕翼型前缘的实心部分; 附接到翼型吸力侧的第一翼; 以及附接到翼型的压力侧的第二翼。 第一翼和第二翼中的至少一个翼部延伸至翼的弦的至少约35％。
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Patent Agency Ranking
公开(公告)号：US10400784B2
公开(公告)日：2019-09-03
申请号：US15075705
申请日：2016-03-21
Applicant: United Technologies Corporation
Inventor： Lee Drozdenko , William R. Graves , Michael Li , Maria C. Kirejczyk
Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.
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公开(公告)号：US20170023010A1
公开(公告)日：2017-01-26
申请号：US15039929
申请日：2014-11-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lee Drozdenko , James O. Hansen , Jesse C. Meyer , Maria C. Kirejczyk , Scot A. Webb , Brandon A. Gates , Richard B. Bergethon
CPC classification number: F04D29/388 , B32B5/024 , B32B7/12 , B32B15/14 , B32B15/20 , B32B2262/101 , B32B2603/00 , F01D5/12 , F01D5/14 , F01D5/147 , F01D5/28 , F01D5/282 , F01D5/286 , F01D5/288 , F04D29/023 , F04D29/325 , F05D2220/36 , F05D2240/303 , F05D2300/121 , F05D2300/133 , F05D2300/6012
Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.
Abstract translation: 叶片包括从后缘延伸到前缘的翼型件。 翼型件包括由含铝材料形成的主体。 护套位于前缘，由含钛材料形成。 三明治位于护套和翼型体之间，夹层包括邻近护套的外部粘合剂层，中间织物层和邻近身体的内部粘合剂层。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US20160348689A1
公开(公告)日：2016-12-01
申请号：US15075705
申请日：2016-03-21
Applicant: United Technologies Corporation
Inventor： Lee Drozdenko , William R. Graves , Michael Ll , Maria C. Kirejczyk
CPC classification number: F04D29/34 , F01D5/30 , F01D5/3007 , F01D21/045 , F02C3/04 , F02K3/06 , F04D29/322 , F04D29/38 , F05D2220/323 , F05D2220/36 , F05D2230/10 , F05D2240/35 , F05D2250/241 , F05D2250/291 , F05D2250/294 , F05D2260/941
Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.
Abstract translation: 提供了一种风扇叶片，其包括前缘，在前缘的后方延伸的附着根和形成在附接根部的表面中的沟槽。 还提供附件根。 附接根部包括前缘，在前缘的后方延伸的燕尾榫和形成在燕尾榫的表面中的沟槽。 还提供燃气涡轮发动机。 燃气涡轮发动机包括被构造成围绕轴线旋转的压缩机部分，压缩机部分的燃烧器后部和压缩机部分的涡轮部分并被构造成围绕轴线旋转。 风扇可以设置在涡轮部分的前方并且包括叶片。 叶片可以具有形成在附接根部中的沟槽。
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公开(公告)号：US20150233259A1
公开(公告)日：2015-08-20
申请号：US14429029
申请日：2013-03-15
Applicant: Sean A. WHITEHURST , Patrick James MCCOMB , Lee DROZDENKO , UNITED TECHNOLOGIES CORPORATION
Inventor： Sean A. Whitehurst , Patrick James McComb , Lee Drozdenko
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.
Abstract translation: 叶片具有从燕尾径向向外延伸的翼型件。 当叶片安装在转子内时，燕尾形的边缘将处于叶片的周向侧。 当转子叶片安装在转子中时，燕尾形的底面将向内径向向内，并且形成为使得底表面的周向中心部分比圆周边缘径向厚。 还描述了风扇和燃气涡轮发动机。
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公开(公告)号：US10801515B2
公开(公告)日：2020-10-13
申请号：US16245484
申请日：2019-01-11
Applicant: United Technologies Corporation
Inventor： Lee Drozdenko , William R. Graves , Michael Li , Maria C. Kirejczyk
Abstract: A fan blade is provided and comprises a leading edge, an attachment root extending aft of the leading edge, and a trench formed in a surface of the attachment root. An attachment root is also provided. The attachment root comprises a leading edge, a dovetail extending aft of the leading edge, and a trench formed in a surface of the dovetail. A gas turbine engine is also provided. The gas turbine engine comprises a compressor section configured to rotate about an axis, a combustor aft of the compressor section, and a turbine section aft of the compressor section and configured to rotate about the axis. A fan may be disposed forward of the turbine section and include a blade. The blade may have a trench formed in an attachment root.
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