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公开(公告)号：US20150192144A1
公开(公告)日：2015-07-09
申请号：US14508774
申请日：2014-10-07
Applicant: United Technologies Corporation
Inventor： James R. Murdock , Mark Quinn
CPC classification number: F04D29/322 , F01D5/323 , F05D2220/36 , Y10T29/49321
Abstract: A fan assembly is disclosed which includes a rotor having an outer periphery and at least one slot extending radially inwardly through the outer periphery. The slot terminates at a base surface disposed at a radial depth from the outer periphery of the rotor. The fan assembly also includes at least one fan blade that includes an airfoil connected to a root. The root is received in the slot. The root terminates in an inner face having a radial length that is less than the radial depth of the Slot to define a gap between the inner face of the root and the base surface of the slot when the root is bias away to the base surface of the slot. A spacer is disposed within a gap, wherein a spacer is fabricated from a polymer, which may be a composite material such as a polymer embedded with reinforcing materials such as carbon fibers and glass fibers.
Abstract translation: 公开了一种风扇组件，其包括具有外周边的转子和至少一个沿着外周向径向向内延伸的槽。 该槽终止于设置在距转子外周的径向深度的基面上。 风扇组件还包括至少一个风扇叶片，其包括连接到根部的翼型件。 根被收到在插槽中。 根部终止于径向长度小于插槽的径向深度的内表面，以限定根部的内表面与槽的基面之间的间隙，当根部偏离到基部的基部表面时 插槽。 间隔件设置在间隙内，其中间隔件由聚合物制成，聚合物可以是复合材料，例如嵌入增强材料如碳纤维和玻璃纤维的聚合物。
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公开(公告)号：US10563666B2
公开(公告)日：2020-02-18
申请号：US15341356
申请日：2016-11-02
Applicant: United Technologies Corporation
Inventor： James R. Murdock
Abstract: A fan for a gas turbine engine is provided. The fan having: a rotor; a hollow fan blade having a cavity, the hollow fan blade secured to the rotor; a cover covering the cavity; a platform independent of the hollow fan blade and secured to the rotor, wherein a portion of the cover is located below a peripheral edge of the platform and the peripheral edge retains the portion of the cover in a desired location.
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公开(公告)号：US20190076970A1
公开(公告)日：2019-03-14
申请号：US15702531
申请日：2017-09-12
Applicant: United Technologies Corporation
Inventor： Michael F. Machinchick , Luke H. Rettberg , Andrew L. Haynes , Janet M. Stanley , Vasisht Venkatesh , David Ulrich Furrer , James R. Murdock , Daniel Gynther , Michael J. Linden
Abstract: Disclosed is a method of making an integrally bladed rotor. According to the method, a rotor disk comprising a radially outer rim surface is provided. A portion of the disk outer rim surface is removed, leaving a protrusion on the rotor disk outer rim surface. The disk with material removed is subjected to thermal processing. A blade comprising an airfoil and a base is positioned such that a base surface is in contact with the protrusion, and heat, pressure, and motion are applied between the blade and the disk to friction weld the base surface to the protrusion.
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公开(公告)号：US20180119707A1
公开(公告)日：2018-05-03
申请号：US15341356
申请日：2016-11-02
Applicant: United Technologies Corporation
Inventor： James R. Murdock
Abstract: A fan for a gas turbine engine is provided. The fan having: a rotor; a hollow fan blade having a cavity, the hollow fan blade secured to the rotor; a cover covering the cavity; a platform independent of the hollow fan blade and secured to the rotor, wherein a portion of the cover is located below a peripheral edge of the platform and the peripheral edge retains the portion of the cover in a desired location.
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公开(公告)号：US20160024947A1
公开(公告)日：2016-01-28
申请号：US14774000
申请日：2013-12-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James R. Murdock , Kwan Hui
Abstract: A blade assembly comprises a blade (120) and one or more wear pads (170, 172). The blade has an airfoil (122) having a leading edge (126), a trailing edge (128), a pressure side (130), a suction side (132), and extending from an inboard end to a tip (125). The blade further includes an attachment root (124). The one or more wear pads are along the attachment root. The one or more wear pads have a plurality of slits (228, 230 242).
Abstract translation: 叶片组件包括叶片（120）和一个或多个耐磨垫（170,172）。 叶片具有一个具有前缘（126），后缘（128），压力侧（130），吸力侧（132）并且从内侧端部延伸到尖端（125）的翼型件（122）。 刀片还包括附件根部（124）。 一个或多个耐磨垫沿着附件根部。 一个或多个磨损垫具有多个狭缝（228,230,242）。
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Patent Agency Ranking
公开(公告)号：US20160003062A1
公开(公告)日：2016-01-07
申请号：US14770256
申请日：2013-12-18
Applicant: United Technologies Corporation
Inventor： James R. Murdock
IPC: F01D5/28
CPC classification number: F01D5/286 , F01D5/147 , F04D29/324 , F05D2220/10 , F05D2220/36 , F05D2230/23 , F05D2230/60 , F05D2240/303 , F05D2240/304 , F05D2300/133 , F05D2300/173 , F05D2300/174 , F05D2300/43 , F05D2300/601 , F05D2300/6012 , Y02T50/672 , Y02T50/673
Abstract: Light weight fan blades for turbofan jet engines are disclosed. The fan blades may be fabricated from an aluminum alloy. To enhance the hardness of the leading edge of the fan blade, a titanium sheath may be attached to the leading edges of the fan blades. To prevent galvanic coupling between the titanium and the aluminum, a polymeric liner may be disposed between the protective titanium sheath and the aluminum fan blade. The liner may be fabricated from a polymer material, such as a polyimide or another high performance polymer.
Abstract translation: 公开了用于涡轮风扇喷气发动机的轻型风扇叶片。 风扇叶片可以由铝合金制成。 为了提高风扇叶片的前缘的硬度，可以将钛护套附接到风扇叶片的前缘。 为了防止钛和铝之间的电偶合，聚合物衬里可以设置在保护性钛护套和铝风扇叶片之间。 衬里可以由聚合物材料制成，例如聚酰亚胺或其它高性能聚合物。
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公开(公告)号：US20150132134A1
公开(公告)日：2015-05-14
申请号：US14400929
申请日：2014-02-21
Applicant: United Technologies Corporation
Inventor： James R. Murdock
CPC classification number: F01D25/28 , B29C45/0005 , B29K2077/00 , B29K2079/085 , B29K2105/12 , B29L2031/08 , F01D5/225 , F01D5/282 , F01D11/008 , F05D2220/32 , F05D2220/36 , F05D2240/90 , F05D2260/30 , F05D2260/36 , F05D2300/43 , F05D2300/603
Abstract: A fan platform for a gas turbine engine may include an outer flow path surface extending between a first side and a second side. An inner surface extends between the first side and the second side, and faces radially oppositely the outer flow path surface. A plurality of platform hooks may extend radially inwardly from the inner surface.
Abstract translation: 用于燃气涡轮发动机的风扇平台可以包括在第一侧和第二侧之间延伸的外部流动路径表面。 内表面在第一侧和第二侧之间延伸，并且面向径向相对的外流路表面。 多个平台钩可以从内表面径向向内延伸。
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公开(公告)号：US10415402B2
公开(公告)日：2019-09-17
申请号：US14774000
申请日：2013-12-20
Applicant: United Technologies Corporation
Inventor： James R. Murdock , Kwan Hui
Abstract: A blade assembly comprises a blade (120) and one or more wear pads (170, 172). The blade has an airfoil (122) having a leading edge (126), a trailing edge (128), a pressure side (130), a suction side (132), and extending from an inboard end to a tip (125). The blade further includes an attachment root (124). The one or more wear pads are along the attachment root. The one or more wear pads have a plurality of slits (228, 230 242).
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公开(公告)号：US10280759B2
公开(公告)日：2019-05-07
申请号：US15163933
申请日：2016-05-25
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： James R. Murdock
Abstract: A blade assembly may be configured to rotate about an axis of a gas turbine engine. The blade assembly may include a blade and a blade cover. A blade may include a first surface defining a perimeter of a cavity in the blade. A first portion of the perimeter of the cavity includes a lip. A blade cover disposed over the cavity in the blade, such that the cavity is disposed between the blade and the blade cover, and under the lip, such that blade cover is between a portion of the blade and the cavity.
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公开(公告)号：US20180202299A1
公开(公告)日：2018-07-19
申请号：US15408882
申请日：2017-01-18
Applicant: United Technologies Corporation
Inventor： James R. Murdock , James H. Moffitt , Scot A. Webb , Jay Thomas Abraham , Maria C. Kirejczyk
CPC classification number: F01D5/28 , F01D5/3092 , F04D29/023 , F05D2220/323 , F05D2220/36 , F05D2230/60 , F05D2240/303 , F05D2260/95 , F05D2300/121 , F05D2300/125 , F05D2300/133 , F05D2300/1616 , F05D2300/50 , Y02T50/671
Abstract: A blade for a gas turbine engine. The blade having: an airfoil formed from a first material; a protective sheath disposed on a leading edge of the airfoil, the protective sheath being formed from a second material, the first material being galvanically incompatible with the second material and the first material being less noble than the second material; a non-conductive material disposed between the protective sheath and the airfoil so that they are electrically isolated from each other; a sacrificial anode in contact with the blade, wherein the sacrificial anode is formed from a third material that is less noble than the first material such that it will corrode before the first material if the non-conductive material disposed between the protective sheath and the airfoil is compromised and the first material and the second material are no longer electrically isolated from each other.
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