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41. 发明申请

US20140255187A1 ATTACHMENT FEATURE OF A GAS TURBINE ENGINE BLADE HAVING A CURVED PROFILE 有权
标题翻译：具有弯曲轮廓的气体涡轮发动机叶片的附着特征
公开(公告)号：US20140255187A1
公开(公告)日：2014-09-11
申请号：US14097865
申请日：2013-12-05
申请人： Rolls-Royce Corporation
发明人： Jonathan M. Rivers , Bronwyn Powers
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F01D5/14 , F01D5/3007
摘要： An airfoil member is disclosed having an attachment feature such as a fir tree or dovetail design that includes a curved profile formed from a combination of curves. In one embodiment, the curved profile can be a compound curve formed by a forward curve and a rearward curve that are joined at a point of common tangency. In another embodiment, the curved profile can include curves that do not meet at a common tangency. A cut out can be formed in the curved profile. In some forms, the cut out is formed on a pressure face of the attachment feature.
摘要翻译：公开了一种翼型件，其具有诸如杉树或燕尾设计的附接特征，其包括由曲线的组合形成的弯曲轮廓。在一个实施例中，弯曲轮廓可以是由正向曲线和向后曲线形成的复合曲线，其在公共切线点处相连。在另一个实施例中，弯曲轮廓可以包括在公共切线处不符合的曲线。可以在弯曲轮廓中形成切口。在一些形式中，切口形成在附接特征的压力面上。

42. 发明申请

US20140241893A1 SYSTEM FOR SPECIFYING AN INSTALLATION POSITION OF ROTOR BLADES, SECURING ELEMENT, ROTOR BLADE, TURBOMACHINE, AND METHOD 有权
标题翻译：用于指定转子叶片，安全元件，转子叶片，涡轮机和方法的安装位置的系统
公开(公告)号：US20140241893A1
公开(公告)日：2014-08-28
申请号：US13775115
申请日：2013-02-22
申请人： MTU AERO ENGINES GMBH
发明人： MARCUS WOEHLER
IPC分类号： F01D5/32
CPC分类号： F01D5/323 , F01D5/30 , Y10T29/49321
摘要： A system for specifying an installation position of adjacent rotor blades of a blade row of a turbomachine is disclosed. The system has a plurality of axial securing elements, which have at least two sections with different profile areas for the arrangement in each case between a groove base of a rotor shaft and a blade root, which are joined together by a connecting web at a groove distance from one another, and which have counter-contours on the blade root side for forming in each case a positive-fit pair with the profile areas. Also disclosed are a securing element and a rotor blade for this type of system, a turbomachine having a rotor which has this type of system, and a method for manufacturing this type of rotor.
摘要翻译：公开了一种用于指定涡轮机的叶片排的相邻转子叶片的安装位置的系统。该系统具有多个轴向固定元件，其具有至少两个具有不同轮廓区域的部分，用于在每种情况下在转子轴的槽基座和叶片根部之间的布置，所述槽基座通过连接腹板在凹槽处连接在一起彼此之间的距离，并且在叶片根侧具有相对的轮廓，用于在每种情况下形成与配置区域的正配对。还公开了用于这种类型的系统的固定元件和转子叶片，具有这种类型的系统的转子的涡轮机，以及用于制造这种类型的转子的方法。

43. 发明申请

US20140169973A1 Ni-Based Heat Resistant Alloy, Gas Turbine Component and Gas Turbine 审中-公开
标题翻译：镍基耐热合金，燃气轮机部件和燃气轮机
公开(公告)号：US20140169973A1
公开(公告)日：2014-06-19
申请号：US14178448
申请日：2014-02-12
申请人： Hitachi, Ltd.
发明人： Jun Sato , Shinya Imano , Hiroyuki Doi
IPC分类号： F01D5/28 , F01D5/30 , C22C19/05
CPC分类号： F01D5/28 , C22C19/05 , C22C19/056 , C22F1/10 , F01D5/30 , Y02E20/16
摘要： A Ni-based heat resistant alloy has a composition of, by mass percent, carbon: 0.001 to 0.1%, chromium: 16 to 22%, aluminum: 0.5 to 1.5%, molybdenum: 0.1 to 2.0%, tungsten: 0.1 to 6.0%, niobium: 3.5 to 5.5%, titanium: 0.8 to 3.0%, iron: 16 to 20%, and the balance being nickel and inevitable impurities. A parameter Ps indicating a segregation tendency is in a range of Ps≧−3.5. The parameter Ps is represented by Formula (1). Ps=1.05×Al content+0.6×Ti content−0.8×Nb content−0.3×Mo content (1)
摘要翻译： Ni系耐热合金的碳质量比为0.001〜0.1％，铬：16〜22％，铝：0.5〜1.5％，钼：0.1〜2.0％，钨：0.1〜6.0％，铌：3.5〜5.5％，钛：0.8〜3.0％，铁：16〜20％，余量为镍和不可避免的杂质。表示偏析倾向的参数Ps在Ps≥-3.5的范围内。参数Ps由公式（1）表示。 Ps = 1.05×Al含量+ 0.6×Ti含量-0.8×Nb含量-0.3×Mo含量（1）

44. 发明授权

US08740567B2 Reverse cavity blade for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的反向腔叶片
公开(公告)号：US08740567B2
公开(公告)日：2014-06-03
申请号：US12843832
申请日：2010-07-26
申请人： Gabriel L. Suciu , James D. Hill , Gary M. Stetson
发明人： Gabriel L. Suciu , James D. Hill , Gary M. Stetson
IPC分类号： F01D5/14 , B23P15/02 , F01D5/18 , F01D5/22 , F01D5/30
CPC分类号： F01D5/147 , F01D5/18 , F01D5/225 , F01D5/30 , F05D2220/321 , Y10T29/49318 , Y10T29/49336
摘要： A rotor blade for a turbine engine includes an airfoil section which extends from a platform section opposite a root section, the airfoil section defines a cavity which extends from an airfoil tip section toward a root section.
摘要翻译：用于涡轮发动机的转子叶片包括从与根部相对的平台部分延伸的翼型部分，翼型部分限定从翼型部分朝向根部部分延伸的空腔。

45. 发明授权

US08720057B2 Method for reconditioning a rotor of a turbomachine 失效
标题翻译：涡轮机转子的修复方法
公开(公告)号：US08720057B2
公开(公告)日：2014-05-13
申请号：US13567542
申请日：2012-08-06
申请人： Ulrich Wellenkamp , Luis Federico Puerta , Wolfgang Kappis
发明人： Ulrich Wellenkamp , Luis Federico Puerta , Wolfgang Kappis
IPC分类号： B23P6/00
CPC分类号： F01D5/005 , B23P6/002 , F01D5/30 , F01D5/3053 , F05D2230/80
摘要： A method is provided for reconditioning a turbomachine rotor, equipped with circumferentially extending grooves for accommodating blades retained in the grooves at a distance from each other by spacers. The method includes removing the blades and spacers from the grooves and hollowing out the exposed grooves, simultaneously widening the grooves to remove damage-inflicted material. At least one circumferentially extending lateral groove is introduced for accommodating a filler piece in the grooves to fill a gap between blades and hollowed-out rotor grooves. New spacers are provided which are matched to the hollowed-out grooves and have recesses which are matched to the introduced lateral grooves. Filler pieces are provided for inserting into the circumferentially extending lateral grooves and recesses of the new spacers. The blades and new spacers are inserted into the hollowed-out rotor grooves and corresponding filler pieces are inserted into the lateral grooves and matched recesses of the new spacers.
摘要翻译：提供了一种用于修复涡轮机转子的方法，该涡轮机转子装备有周向延伸的槽，用于容纳通过间隔件彼此间隔开的保持在槽中的刀片。该方法包括从凹槽中移除叶片和间隔物并挖出暴露的凹槽，同时加宽凹槽以除去损坏的材料。引入至少一个周向延伸的横向槽，用于在槽中容纳填充件以填充叶片和中空的转子槽之间的间隙。提供了新的间隔件，其与掏空的凹槽匹配，并且具有与引入的横向凹槽匹配的凹部。填充件被设置成插入到新间隔件的周向延伸的横向槽和凹槽中。叶片和新的间隔件被插入到中空的转子槽中，并且相应的填充件插入到新间隔件的横向槽和匹配的凹部中。

46. 发明申请

US20140127025A1 WIND TURBINE ROTOR BLADE AND METHOD FOR INSTALLING A WIND TURBINE ROTOR BLADE 有权
标题翻译：风力涡轮机转子叶片及其安装风力发电机转子叶片的方法
公开(公告)号：US20140127025A1
公开(公告)日：2014-05-08
申请号：US14123443
申请日：2012-05-29
申请人： Alexander Hoffmann
发明人： Alexander Hoffmann
IPC分类号： F01D5/30
CPC分类号： F01D5/30 , F03D13/10 , F05B2230/60 , F05B2230/61 , F05B2230/70 , Y02B10/30 , Y02E10/721 , Y02E10/728 , Y02P70/523 , Y10T29/49336
摘要： There is provided a wind power installation rotor blade having a rotor blade root, a rotor blade tip, a rotor blade leading edge, a rotor blade trailing edge, a pressure side and a suction side. The rotor blade further has a rotor blade outer casing with at least one opening in the pressure and/or suction side for receiving handling means for fitting or removing the rotor blade. The rotor blade also has at least one fixing unit for fixing the handling means which are introduced through the at least one opening. The fixing unit is arranged in the interior of the rotor blade outer casing between the pressure side and the suction side.
摘要翻译：提供了具有转子叶片根部，转子叶片尖端，转子叶片前缘，转子叶片后缘，压力侧和吸力侧的风力设备转子叶片。转子叶片还具有转子叶片外壳，其在压力和/或吸力侧具有至少一个开口，用于接收用于装配或移除转子叶片的处理装置。转子叶片还具有至少一个用于固定通过至少一个开口引入的处理装置的固定单元。固定单元布置在转子叶片外壳的内部，在压力侧和吸力侧之间。

47. 发明申请

US20140116065A1 TURBINE NOZZLE GUIDE IN A TURBINE ENGING 有权
标题翻译：涡轮喷嘴指南在涡轮发动机
公开(公告)号：US20140116065A1
公开(公告)日：2014-05-01
申请号：US14115980
申请日：2012-05-04
申请人： Denis Jean Maurice Sandelis , Didier Hippolyte Hernandez
发明人： Denis Jean Maurice Sandelis , Didier Hippolyte Hernandez
IPC分类号： F02C7/12
CPC分类号： F02C7/12 , F01D5/186 , F01D5/30 , F01D9/023 , F01D9/041 , F05B2240/201 , F05D2240/81 , F05D2260/201 , F05D2260/202 , Y02T50/676
摘要： A sectorized nozzle for a turbine engine turbine including an inner sectorized annular platform and an outer sectorized annular platform connected together by radial airfoils, at least one of the platforms including a plurality of orifices for passing air in a neighborhood of its upstream end, the orifices being distributed over the circumference of the platform and opening out at their ends remote from the airfoils into a circumferential annular cavity of the sector of the platform, which cavity is closed by a metal sheet fastened to the platform sector and pierced by orifices for feeding cooling air.
摘要翻译：一种用于涡轮发动机涡轮机的分段喷嘴，包括内部扇形环形平台和通过径向翼型件连接在一起的外部扇形环形平台，所述平台中的至少一个包括用于在其上游端附近通过空气的多个孔，分布在平台的圆周上并且在其远离翼型的端部处开口，进入平台扇区的周向环形空腔中，该空腔被固定到平台扇区的金属片封闭，并被用于进给冷却的孔空气。

48. 发明授权

US08672630B2 Annular turbine ring rotor 有权
标题翻译：环形涡轮环转子
公开(公告)号：US08672630B2
公开(公告)日：2014-03-18
申请号：US13350937
申请日：2012-01-16
申请人： Gabriel L. Suciu , James W Norris , Craig A. Nordeen , Brian Merry
发明人： Gabriel L. Suciu , James W Norris , Craig A. Nordeen , Brian Merry
IPC分类号： F01D5/06 , F01D5/08 , F01D5/22
CPC分类号： F01D11/02 , F01D5/30
摘要： A fan-turbine rotor assembly includes one or more turbine ring rotors. Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring includes axial installation and radial locking of each turbine ring rotor.
摘要翻译：风扇 - 涡轮转子组件包括一个或多个涡轮机环形转子。每个涡轮机环形转子都被铸造为一个整体的环形环。通过将涡轮机形成为一个或多个环，相邻的叶片平台之间的泄漏最小化，这增加了发动机效率。涡轮环转子到扩散器环的组装包括每个涡轮环转子的轴向安装和径向锁定。

49. 发明申请

US20140044547A1 ROTATABLE BLADE APPARATUS WITH INDIVIDUALLY ADJUSTABLE BLADES 审中-公开
标题翻译：可旋转叶片装置，具有独立可调节刀片
公开(公告)号：US20140044547A1
公开(公告)日：2014-02-13
申请号：US14050532
申请日：2013-10-10
申请人： ENERGYIELD LLC
发明人： Robert Hotto
IPC分类号： F01D5/30
CPC分类号： F03D7/0224 , B64C11/30 , F01D5/30 , F03D1/0608 , F03D1/0675 , F03D7/00 , F03D7/0236 , F03D7/024 , F05B2240/202 , F05B2240/2021 , F05B2240/31 , F05B2240/312 , F05B2240/313 , Y02E10/721 , Y02E10/723
摘要： The lengths and/or chords and/or pitches of wind turbine or propeller blades are individually established, so that a first blade can have a length/chord/pitch that is different at a given time to the length/chord/pitch of a second blade to optimize performance and/or to equalize stresses on the system.
摘要翻译：风力涡轮机或螺旋桨叶片的长度和/或弦和/或间距被单独建立，使得第一叶片可以具有在给定时间与第二叶片的长度/弦/间距不同的长度/弦/间距刀片以优化性能和/或平衡系统上的应力。

50. 发明申请

US20140003949A1 INTERBLADE PLATFORM FOR A FAN, ROTOR OF A FAN AND ASSOCIATED MANUFACTURING METHOD 审中-公开
标题翻译：风扇横梁平台，风扇转子及相关制造方法
公开(公告)号：US20140003949A1
公开(公告)日：2014-01-02
申请号：US13926316
申请日：2013-06-25
申请人： SNECMA
发明人： Virginie ADAM , Guillaume Fribourg
IPC分类号： F01D11/00
CPC分类号： F01D11/008 , C22C21/00 , C22C21/10 , C22C21/12 , C22C21/18 , F01D5/02 , F01D5/28 , F01D5/30 , F01D5/3007 , F01D11/005 , Y02T50/671 , Y02T50/673 , Y10T29/49321
摘要： The invention concerns an interblade platform (3) of a turbomachine fan, characterized in that it is produced:in an aluminum alloy belonging to the 7xxx series that has undergone full-temper heat treatment of the T7x type, orin an aluminum alloy belonging to the 2xxx series that has undergone heat treatment of the T6x or T8x type.
摘要翻译：本发明涉及一种涡轮机风扇的叶片间平台（3），其特征在于：在属于经过T7x型全温热处理的属于7xxx系列的铝合金中，或属于属于经过T6x或T8x型热处理的2xxx系列。

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