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21. 发明授权

US09598961B2 Gas turbine spindle bolt structure with reduced fretting fatigue 有权
公开(公告)号：US09598961B2
公开(公告)日：2017-03-21
申请号：US14330323
申请日：2014-07-14
申请人： Siemens Energy, Inc.
发明人： Manish S. Gurao , Kevin M. Light , Zafir A. M. Abdo , Kazim Ozbaysal
IPC分类号： F01D5/06 , F01D5/02 , F01D11/02 , F04D29/64 , F04D29/054 , F01D5/30
CPC分类号： F01D5/066 , F01D5/025 , F01D5/30 , F01D11/025 , F04D29/054 , F04D29/644 , F05D2230/10 , F05D2260/31 , F05D2260/941 , F05D2300/5021
摘要： A spindle bolt structure is provided in a gas turbine engine, and includes a pilot region located within a bolt hole extending through a seal disk. The pilot region includes a circumferential pilot ridge located adjacent to a downstream axial face of the seal disk and a circumferential trough portion located between a bolt shoulder and the pilot ridge. The trough portion defines a trough diameter that is less than a diameter of the bolt shoulder and less than a diameter of the pilot ridge. The bolt shoulder and pilot ridge are formed with an applied compressive residual stress and are positioned for engagement with the seal disk.

22. 发明授权

US09555592B2 Method for manufacturing a turbine engine blade root of a composite material and blade root obtained by such a method 有权
标题翻译：通过这种方法获得的复合材料和叶片根部的涡轮发动机叶片根部的制造方法
公开(公告)号：US09555592B2
公开(公告)日：2017-01-31
申请号：US14648762
申请日：2013-12-03
申请人： SNECMA
发明人： Hubert Illand
IPC分类号： B29D99/00 , F01D5/14 , F01D5/30 , B29C70/42 , B29C70/24 , D03D25/00 , F01D5/28 , B29L31/08
CPC分类号： B29D99/0025 , B29B11/16 , B29C70/24 , B29C70/42 , B29L2031/082 , D03D25/005 , F01D5/147 , F01D5/282 , F01D5/284 , F01D5/30 , F01D5/3007 , F01D5/3084 , F05D2220/30 , F05D2230/31 , F05D2240/30 , F05D2300/603 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A method of fabricating a turbine engine blade root out of composite material including fiber reinforcement densified by a matrix, the method including making a central fiber strip and two outer fiber strips from three sets of yarn layers interlinked by three-dimensional weaving, passing the two outer strips through the central strip with the two outer strips crossing each other inside the central strip, eliminating the portions of the two outer strips lying outside the central strip by cutting them off, shaping the fiber blank in order to obtain a preform having a main portion forming a blade-root preform integral with two secondary portions forming bearing-plate preforms, and densifying the preform densified by the matrix.
摘要翻译：一种制造由包括由基体致密化的纤维增强材料的复合材料制成的涡轮发动机叶片根部的方法，该方法包括由三组织纱相互连接的三组纱线层组成中心纤维条和两条外部纤维条，外部条带穿过中央条带，其中两个外部条带在中心条带内部彼此交叉，通过切除它们而将两个外部条带的部分位于中央条带的外侧，使纤维坯料成形以获得具有主体的预成型件形成与形成支承板预成型件的两个二次部分成一体的叶根根部预成型件的部分，并且致密化由基体致密化的预制件。

23. 发明授权

US09546551B2 Repaired turbine rotor wheel dovetail and related method 有权
标题翻译：涡轮转子轮蜗杆修理及相关方法
公开(公告)号：US09546551B2
公开(公告)日：2017-01-17
申请号：US14028970
申请日：2013-09-17
申请人： General Electric Company
发明人： Benedict Kazirskis , Lawrence Michael Grycko
IPC分类号： F01D5/02 , B23P6/00 , F01D5/00 , F01D5/06 , F01D5/30 , B23K31/02
CPC分类号： F01D5/005 , B23K31/02 , B23K2101/001 , B23P6/005 , F01D5/02 , F01D5/06 , F01D5/063 , F01D5/30 , F01D5/303 , F01D5/3053 , F05D2220/31 , F05D2220/32 , F05D2230/232 , F05D2230/80 , F05D2240/24 , Y10T29/49318
摘要： A method of repairing a damaged dovetail on a peripheral portion of a turbine wheel includes the steps of removing buckets from the dovetail; removing a damaged dovetail from the peripheral portion of the turbine wheel, leaving a rotor wheel body having a peripheral rim; disposing a replacement ring about the peripheral rim, the replacement ring and the rim defining therebetween a pair of end grooves and a center section; and welding the replacement ring to the peripheral rim, with weld material applied only within the end grooves, leaving a void in the center section.
摘要翻译：在涡轮机叶轮的周边部分修复损坏的燕尾的方法包括以下步骤：从燕尾槽移除桶; 从涡轮机轮的周边部分去除损坏的燕尾榫，留下具有外围边缘的转子轮体; 在外围边缘上设置更换环，更换环和轮缘在其间限定一对端槽和中心部分; 并将替换环焊接到周边边缘，焊接材料仅在端槽内施加，在中心部分留下空隙。

24. 发明授权

US09523281B2 Blade for a wind turbine 有权
标题翻译：风力发电机叶片
公开(公告)号：US09523281B2
公开(公告)日：2016-12-20
申请号：US13880961
申请日：2011-11-10
申请人： Luca Feigl
发明人： Luca Feigl
IPC分类号： F03D11/00 , F01D5/30 , F03D1/00 , F03D1/06
CPC分类号： F01D5/30 , F03D1/0658 , F03D13/10 , F03D80/00 , F05B2230/604 , Y02E10/721 , Y02E10/728 , Y02P70/523 , Y10T29/49336
摘要： A blade for a wind turbine comprising a blade root portion for attachment to a mounting flange of the wind turbine, the blade root comprising a plurality of first holes provided with an internal bushing wherein the bushings comprise a first end at or near a mounting surface of the blade root and an opposite second end embedded in their corresponding first holes, and wherein one or more internal bushing being guiding bushings, the guiding bushings comprising a first end that is adapted to guide the blade root with respect to a mounting flange.
摘要翻译：一种用于风力涡轮机的叶片，包括用于附接到风力涡轮机的安装凸缘的叶片根部部分，叶片根部包括设置有内部衬套的多个第一孔，其中衬套包括位于或接近安装表面的第一端叶片根部和相对的第二端部嵌入其相应的第一孔中，并且其中一个或多个内部衬套是引导衬套，所述引导衬套包括适于相对于安装凸缘引导叶片根部的第一端。

25. 发明申请

US20160319670A1 Turbomachine Blade 审中-公开
标题翻译：涡轮机刀片
公开(公告)号：US20160319670A1
公开(公告)日：2016-11-03
申请号：US15211510
申请日：2016-07-15
申请人： United Technologies Corporation
发明人： Bryan C. Atkins , Robert J. Esteve , Richard A. Lomenzo, JR. , David P. Houston
IPC分类号： F01D5/16 , F01D5/30 , F01D5/18
CPC分类号： F01D5/16 , F01D5/14 , F01D5/141 , F01D5/186 , F01D5/30 , F05D2220/32 , F05D2240/30 , F05D2260/202 , F05D2300/175 , Y02T50/673
摘要： A turbomachine airfoil element has an airfoil. The airfoil has an inboard end, an outboard end, a leading edge, a trailing edge, a pressure side, and a suction side. A span between the inboard and an outboard end is 1.4-1.6 inch. A chord length at 50% span is 0.9-1.4 inch. At least three of the following resonance frequencies are present. A first mode resonance frequency is 2591.5±10% Hz. A second mode resonance frequency is 4675.2±10% Hz. A third mode resonance frequency is 7892.9±10% Hz. A fourth mode resonance frequency is 10098.2±10% Hz. A fifth mode resonance frequency is 14808.2±10% Hz.
摘要翻译：涡轮机翼型元件具有翼型。翼型件具有内侧端部，外侧端部，前缘部，后缘部，压力侧部和吸力侧。内侧和外侧之间的距离为1.4-1.6英寸。 50％跨度的弦长为0.9-1.4英寸。存在以下共振频率中的至少三个。第一模式谐振频率为2591.5±10％Hz。第二模式谐振频率为4675.2±10％Hz。第三模式谐振频率为7892.9±10％Hz。第四模式谐振频率为10098.2±10％Hz。第五种谐振频率为14808.2±10％Hz。

26. 发明申请

US20160298460A1 ROTOR DAMPER 审中-公开
标题翻译：转子阻尼器
公开(公告)号：US20160298460A1
公开(公告)日：2016-10-13
申请号：US15094415
申请日：2016-04-08
申请人： ROLLS-ROYCE PLC
发明人： Michael F BRYANT , Garry M. EDWARDS
IPC分类号： F01D5/10
CPC分类号： F01D5/10 , F01D5/16 , F01D5/30 , F01D5/34 , F05D2220/32 , F05D2240/20 , F05D2240/80 , F05D2260/96
摘要： A rotor stage (100) of a gas turbine engine (10) comprises a platform (120) from which rotor blades extend. The platform is provided with a circumferentially extending damper ring (200), the damper ring having an engagement surface (210) that engages with a platform engagement surface (110) of the platform (120). In use, the damper engagement surface (210) and the platform engagement surface (110) move relative to each other in a radial direction, in response to diametral mode excitation. This causes friction between the two surfaces, thereby dissipating energy and damping the excitation. The rotor stage (100) is arranged such that the engagement load between the damper engagement surface (210) and the platform engagement surface (110) is a function of the rotational speed of the rotor stage (100).
摘要翻译：燃气涡轮发动机（10）的转子平台（100）包括转子叶片延伸的平台（120）。平台设置有周向延伸的阻尼环（200），阻尼环具有与平台（120）的平台接合表面（110）接合的接合表面（210）。在使用中，响应于直径模式激励，阻尼器接合表面（210）和平台接合表面（110）在径向方向上相对于彼此移动。这导致两个表面之间的摩擦，从而消耗能量并阻尼激励。转子级（100）被布置成使得阻尼器接合表面（210）和平台接合表面（110）之间的接合负载是转子级（100）的旋转速度的函数。

27. 发明授权

US09464530B2 Turbine bucket and method for balancing a tip shroud of a turbine bucket 有权
标题翻译：涡轮斗和平衡涡轮叶片顶端护罩的方法
公开(公告)号：US09464530B2
公开(公告)日：2016-10-11
申请号：US14185161
申请日：2014-02-20
申请人： General Electric Company
发明人： Spencer Aaron Kareff , Matthew Robert Piersall , Danielle Werner
IPC分类号： F01D5/30 , F01D5/20 , F01D5/22
CPC分类号： F01D5/30 , F01D5/20 , F01D5/225 , Y02T50/671
摘要： The present application and the resultant patent provide a turbine bucket for a gas turbine engine. The turbine bucket may include an airfoil, a tip shroud positioned radially outward from the airfoil, and a seal rail positioned radially outward from the tip shroud and extending in a generally tangential direction from a first end to a second end of the tip shroud. The seal rail may include a maximum axial thickness at a location positioned between the first end and the second end and offset from the airfoil in the generally tangential direction. The present application and the resultant patent further provide a gas turbine engine and a method for balancing a tip shroud of a turbine bucket of a gas turbine engine.
摘要翻译：本申请和所得专利提供了一种用于燃气涡轮发动机的涡轮机桶。涡轮机桶可以包括翼型，从翼型件径向向外定位的尖端护罩，以及从尖端护罩径向向外定位并沿大致切线方向从尖端护罩的第一端延伸到第二端的密封轨道。密封导轨可以在位于第一端和第二端之间的位置处包括最大轴向厚度，并且在大致切线方向上偏离翼型。本申请和所得到的专利进一步提供了一种燃气涡轮发动机和用于平衡燃气涡轮发动机的涡轮机叶片的尖端护罩的方法。

28. 发明授权

US09441493B2 Fixture and method for securing an aerofoil 有权
标题翻译：用于固定机翼的夹具和方法
公开(公告)号：US09441493B2
公开(公告)日：2016-09-13
申请号：US13973464
申请日：2013-08-22
申请人： ROLLS-ROYCE PLC
发明人： Christopher Alan Simmons , Mark David Hancock , Andrew Mantle
IPC分类号： F01D5/30 , B23Q3/06 , B23Q1/03 , B23Q17/22
CPC分类号： F01D5/30 , B23Q1/035 , B23Q3/063 , B23Q17/2233 , Y10T29/4932
摘要： A fixture having a foot clamp for clamping a foot of an aerofoil and a tip clamp for clamping a tip of the aerofoil is provided with an array of supports between the foot clamp and the tip clamp. Each support within the array is independently addressable to one of the aerofoil flanks when the aerofoil is secured to the fixture. The support is driven by pneumatics till it contacts the aerofoil when it is locked by an alternative mechanism.
摘要翻译：具有用于夹紧翼面的脚部的脚夹具和用于夹紧机翼的尖端的尖端夹具的夹具在脚夹和尖端夹具之间设置有支撑体阵列。当机翼固定到固定装置上时，阵列内的每个支撑件可以独立地寻址到其中一个翼面侧面。支撑由气动驱动，直到它通过替代机构锁定时接触机翼。

29. 发明授权

US09382805B2 Balancing of rotors 有权
标题翻译：平衡转子
公开(公告)号：US09382805B2
公开(公告)日：2016-07-05
申请号：US13751810
申请日：2013-01-28
申请人： ROLLS-ROYCE PLC
发明人： Alexander Lewis Shaw
IPC分类号： F01D5/30 , F04D29/32 , F01D5/02 , F04D29/66
CPC分类号： F01D5/30 , F01D5/027 , F01D5/303 , F01D5/3038 , F04D29/321 , F04D29/662 , Y10T29/49316
摘要： A balanced rotor comprising a circumferential slot and a plurality of aerofoils each secured in the slot by a respective root, the root having a root block having circumferentially facing flanks and a seal wing extending circumferentially from one of the flanks, characterized in that the seal wing has a notch engaging a balance weight positioned between adjacent roots.
摘要翻译：平衡转子，其包括周向狭槽和多个翼型件，每个翼型件分别通过相应的根部固定在所述槽中，所述根部具有根部块，所述根部具有周向面向的侧面和从所述侧面中的一个周向延伸的密封翼，其特征在于，所述密封翼具有接合位于相邻根之间的平衡重的凹口。

30. 发明申请

US20160186713A1 TURBINE ROTOR ASSEMBLY 审中-公开
公开(公告)号：US20160186713A1
公开(公告)日：2016-06-30
申请号：US15062722
申请日：2016-03-07
申请人： WAVE POWER RENEWABLES LIMITED
发明人： Peter John MURDOCH
IPC分类号： F03B3/14 , F03B3/12 , F03B3/06 , F03B13/14 , F03B11/02
CPC分类号： F03B3/145 , F01D5/30 , F03B3/06 , F03B3/128 , F03B11/02 , F03B13/142 , F05B2210/404 , Y02E10/32 , Y02E10/38
摘要： A turbine rotor assembly for extracting energy from an oscillating working fluid. The turbine rotor assembly includes a hub rotatable about a central axis. A plurality of blades is mounted to the hub about the central axis. Each blade has a leading edge and a trailing edge which are configured to be complementary in profile to each other such that the blades can be mounted in close fitting edge-to-edge proximity to each other.

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