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1. 发明专利

JP2011153619A Method and device for strengthening surface of blade of blisk 有权
标题翻译：用于加强BLISK叶片表面的方法和装置
公开(公告)号：JP2011153619A
公开(公告)日：2011-08-11
申请号：JP2010269250
申请日：2010-12-02
申请人： Rolls-Royce Deutschland Ltd & Co Kg , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： HENNIG WOLFGANG , FELDMANN GOETZ G
IPC分类号： F02C7/00 , B23P17/00 , F01D5/28 , F04D29/32
CPC分类号： B23P9/04 , C21D7/04 , F05B2230/90
摘要： PROBLEM TO BE SOLVED: To provide a method and a device for strengthening surfaces of blade of a blisk.
SOLUTION: A zone of the whole or at least a part of processing blades regarding the blades of the blisk to be processed is inserted into a water tank (13), and numbers of jets (10) of high-pressure water facing both sides of each blade and substantially and oppositely facing each other at a right angle or an slanting state to both sides of each blade are injected into the water tank so as to effect cavitation foams (11) which are generated near the jets of the high-pressure water in the water tank and explode in the vicinity of the surfaces of each blade. Minute jets (12) caused by explosion of the cavitation foams take effect on the surfaces of each blade, and such minute jets create plastically-formed dents (14) with no sharp edges.
COPYRIGHT: (C)2011,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于加强叶片叶片表面的方法和装置。解决方案：将要处理的叶片的叶片的整个或至少一部分处理叶片的区域插入水箱（13）中，并且将数量的高压水面（10）每个叶片的两侧并且在每个叶片的两侧以直角或倾斜状态彼此相对地相对地注入到水箱中，以便实现在高压喷嘴附近产生的空化泡沫（11） - 在水箱中压水，并在每个叶片的表面附近爆炸。由气蚀泡沫爆炸引起的分钟喷气（12）在每个叶片的表面上起作用，这种分针可形成没有锋利边缘的塑性成形凹部（14）。版权所有（C）2011，JPO＆INPIT

2. 发明专利

JP2010172963A Apparatus for repairing blade of brisk drum by welding using laser vapor deposition 有权
标题翻译：通过使用激光蒸气沉积的焊接来修复玻璃丝刀片的装置
公开(公告)号：JP2010172963A
公开(公告)日：2010-08-12
申请号：JP2010002660
申请日：2010-01-08
申请人： Rolls-Royce Deutschland Ltd & Co Kg , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： ZHU LEPING
IPC分类号： B23K26/34 , B23K9/00 , B23K26/02 , B23K26/08 , B23K26/14 , B23K31/00 , F01D25/00 , F02C7/00
CPC分类号： B23K26/03 , B23K26/1482 , B23K26/342 , B23K2201/001 , F01D5/005 , F05D2230/234 , Y02T50/671 , Y10T29/49238 , Y10T29/49318 , Y10T29/49325
摘要： PROBLEM TO BE SOLVED: To provide an apparatus for repairing blades of BRISK drums for gas turbines by welding using laser vapor deposition. SOLUTION: The apparatus is provided with a module 13 which is connected to a laser source and in which a laser beam is deflected in the longitudinal direction. The module 13 is connected to a module for a CCD camera 12. The CCD camera enables the apparatus to be positioned and the deposition of the powder on blades to be monitored and controlled. A module 19 for shaping and focusing the laser beam, and a module 20 are adjoining the side of the module 13 opposite the camera module. A supply line 35 connected to a weld powder feeder disposed in a head 21 in the longitudinal direction in the interior of the module 20, is directed towards an exit port 36. The exit port adjoins to a module 22 which is connected to a gas source and forms a protective-gas duct, in which the blade to be repaired is included, the metal deposit applied to the blade edge is sealed with protective gas, thereby protecting the deposit against deterioration during melting or the like. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于通过使用激光气相沉积焊接来修复用于燃气轮机的BRISK鼓的叶片的装置。解决方案：该装置设置有模块13，模块13连接到激光源，激光束沿纵向方向偏转。模块13连接到用于CCD照相机12的模块。CCD照相机使得能够定位设备并且将粉末沉积在叶片上以被监视和控制。用于使激光束成形和聚焦的模块19和模块20与模块13的与相机模块相对的一侧相邻。连接到在模块20的内部沿长度方向设置在头部21中的焊接粉末进料器的供应管线35被引向出口36.出口与模块22相连，模块22连接到气源并且形成保护气体管道，其中包括要修理的刀片，施加到刀刃的金属沉积物用保护气体密封，从而保护沉积物不会在熔化等期间劣化。版权所有（C）2010，JPO＆INPIT

3. 发明专利

JP2010180877A Method for manufacturing blisk type rotor wheel blade tip 有权
标题翻译：制造BLISK型转子轮叶片的方法
公开(公告)号：JP2010180877A
公开(公告)日：2010-08-19
申请号：JP2010002666
申请日：2010-01-08
申请人： Rolls-Royce Deutschland Ltd & Co Kg , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： ZHU LEPING , RIEDEL GREGOR
IPC分类号： F02C7/00 , F01D1/06 , F01D5/06 , F01D5/30 , F01D25/00
CPC分类号： B23P15/006 , B23C3/18 , B23C2215/44 , B23C2265/08 , B23P13/02 , F01D5/34 , F04D29/324 , F04D29/644 , F05D2230/10 , Y10T29/49325 , Y10T29/49336
摘要： PROBLEM TO BE SOLVED: To provide a method for manufacturing the compressor rotor blade tip of an aircraft gas turbine. SOLUTION: With a method for finish-machining the blade tips 2 of rotor wheels made in BLISK design, in particular of multi-stage compressor rotors 1 for the aircraft gas turbines or industrial gas turbines, the rotor wheel, or also the multi-stage compressor rotor, restrained in a clamping fixture is machined, blade 3 by blade 3 and stage 4 by stage 4, at the blade tips by means of a conical cutter 5 while a cutting edge 7 of the conical cutter is oriented tangentially to the outside surface of the rotor wheel or the compressor rotor and routed on the blade tip essentially along the centerline thereof, with cutting force being introduced vertically to a tool axis 11 and in the stiffest direction of the blade, i.e. the centerline of a blade cross-section and a vertical axis extending from the centerline. The cutting action and force introduction of the conical cutter at the blade tip are such that blade tips with a geometrically precisely defined edge can be produced, thereby dispensing with time-consuming and cost-intensive assembly and disassembly of damping means likely leading to distortion and dimensional deviations of the blades. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于制造飞机燃气轮机的压缩机转子叶片尖端的方法。解决方案：使用用于对BLISK设计的转子轮的叶片尖端2进行精加工的方法，特别是用于飞机燃气轮机或工业燃气轮机的多级压缩机转子1，转子轮，或者夹紧夹具中的多级压缩机转子通过刀片3和阶段4由工作台4通过锥形切割器5在叶片尖端处被加工，同时锥形切割器的切割刃7切向地定向于转子轮或压缩机转子的外表面，并且基本上沿其中心线路线在叶片尖端上，切割力垂直地引导到工具轴线11并且在叶片的最硬方向上，即叶片横截面的中心线和从中心线延伸的垂直轴。锥形切割器在叶片尖端处的切割动作和力的引入使得可以产生具有几何精确限定的边缘的叶片尖端，从而分配耗时且成本高昂的组装和拆卸可能导致变形的阻尼装置，叶片的尺寸偏差。版权所有（C）2010，JPO＆INPIT

4. 发明专利

JP2009297788A Method for manufacturing blisk 有权
标题翻译：制造BLISK的方法
公开(公告)号：JP2009297788A
公开(公告)日：2009-12-24
申请号：JP2009116561
申请日：2009-05-13
申请人： Rolls-Royce Deutschland Ltd & Co Kg , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： SCHREIBER KARL , MOHNKOPF HERMANN
IPC分类号： B23K1/00 , B23K1/005 , B23K1/20 , B23K3/06 , B23K103/18 , F01D5/28 , F01D25/00 , F02C7/00 , F04D29/32
CPC分类号： B23K1/0056 , B23K1/0018 , B23K2201/001 , B23K2203/14 , Y10T29/49337
摘要： PROBLEM TO BE SOLVED: To provide a method for manufacturing integrally bladed rotors by positive-substance joining. SOLUTION: A rotor disk 1 made of a nickel or titanium-base material is connected to blades 3 made of titanium aluminide by way of laser brazing. As brazing material, a material similar to the blade material is used, which is introduced into the laser beam 4 as brazing power jet 5 and whose heat capacity, which is controlled by the melting temperature and the volume of the molten metal bath, provides for melting of the disk material and all alloys with this material, however not for melting of the blade material, to which it is connected by adhesion. Connection is made via blade stubs 2 formed on the rotor disk. The molten metal bath is backed by means of a water-cooled bath support 8. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供通过正物质接合制造整体叶片转子的方法。解决方案：由镍或钛基材料制成的转子盘1通过激光钎焊连接到由铝化钛制成的刀片3上。作为钎焊材料，使用类似于刀片材料的材料，其被引入到激光束4中作为钎焊力喷射5，并且其熔融温度和熔融金属浴体积控制的热容提供使用该材料熔化盘材料和所有合金，然而不能熔化通过粘合而连接到其上的刀片材料。通过形成在转子盘上的刀片坯料2进行连接。熔融金属浴通过水冷浴支撑件8支撑。版权所有（C）2010，JPO＆INPIT

5. 发明专利

JP2009255288A Method for aerodynamically shaping front edge of blisk blade 有权
标题翻译：用于气动叶片前缘形成的方法
公开(公告)号：JP2009255288A
公开(公告)日：2009-11-05
申请号：JP2009089318
申请日：2009-04-01
申请人： Rolls-Royce Deutschland Ltd & Co Kg , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： HOLZE LIANE , RIEDEL GREGOR
IPC分类号： B23C3/18 , B23P15/02 , F01D25/00 , F02C7/00
CPC分类号： B24B19/14 , B23C3/18 , B23C2215/44 , B23P15/006 , F01D5/141 , F01D5/34 , F05D2240/121 , F05D2240/303 , Y10T29/49325 , Y10T29/49336 , Y10T29/49337 , Y10T29/49995 , Y10T29/49996
摘要： PROBLEM TO BE SOLVED: To provide a method for shaping a front edge of a blisk blade machined from a solid, capable constantly and aerodynamically shaping the front edge over an entire length thereof in a variety of embodiments. SOLUTION: For shaping the front edge 1 of the blink blade 2, a shape, an amount and the disposition of a material to be removed in a subsequent grinding and polishing process is determined beforehand over the entire length of the blade. The front edge of the blade is milled so that an elliptical profile 3 has a material allowance 7 which accurately corresponds to a desired material removal over the length of the front edge, thus forming the blisk blade by milling which has the front edge characterized by an aerodynamically advantageous shape. COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于使从固体机加工的叶片叶片的前边缘成形的方法，其能够在各种实施例中在其整个长度上恒定地和空气动力学地成形前边缘。解决方案：为了使眨眼刀片2的前缘1成形，在刀片的整个长度上预先确定在随后的研磨和抛光处理中要除去的材料的形状，数量和布置。刀片的前边缘被铣削，使得椭圆形轮廓3具有材料余量7，其精确地对应于在前边缘的长度上的期望材料去除，从而通过铣削形成叶片刀片，其具有由空气动力学有利的形状。版权所有（C）2010，JPO＆INPIT

6. 发明专利

JP2010196699A Turboprop propulsion device equipped with pusher propeller 审中-公开
标题翻译：带推进螺旋桨的涡轮推进装置
公开(公告)号：JP2010196699A
公开(公告)日：2010-09-09
申请号：JP2010029927
申请日：2010-02-15
申请人： Rolls-Royce Deutschland Ltd & Co Kg , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： NEGULESCU DIMITRIE
IPC分类号： F02C7/20 , F01D25/30 , F02C7/00 , F02C7/04 , F02C7/36
CPC分类号： B64D27/10 , B64D27/14 , B64D33/02 , B64D33/04 , B64D2027/005 , F02C3/145 , F02K3/025 , F02K3/072 , Y02T50/44 , Y02T50/66
摘要： PROBLEM TO BE SOLVED: To provide a turboprop propulsion device having comprehensively high reliability on a propulsion system.
SOLUTION: The turboprop propulsion device includes at least one of pusher propellers 5, 6 to be driven by an aircraft gas turbine engine. The aircraft gas turbine engine is arranged in front of the pusher propellers 5, 6 in the flying direction, a turbine exhaust port part is arranged on the front side in the flying direction, and a compressor part 14 is arranged toward the pusher propellers 5, 6.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供在推进系统上具有全面高可靠性的涡轮螺旋桨推进装置。解决方案：涡轮螺旋桨飞机推进装置包括由飞机燃气涡轮发动机驱动的推进推进器5,6中的至少一个。飞机燃气涡轮发动机沿着飞行方向布置在推进器5,6的前方，涡轮排气口部分沿飞行方向布置在前侧，并且压缩机部分14布置成朝向推进器螺旋桨5， 6.版权所有（C）2010，JPO＆INPIT

7. 发明专利

JP2010151127A Method for manufacturing welding rotor of gas turbine engine 审中-公开
标题翻译：燃气轮机发动机焊接转子的制造方法
公开(公告)号：JP2010151127A
公开(公告)日：2010-07-08
申请号：JP2009274405
申请日：2009-12-02
申请人： Rolls-Royce Deutschland Ltd & Co Kg , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： SCHREIBER KARL , GROSSMANN KIM
IPC分类号： F02C7/00 , F01D5/02 , F01D25/00
CPC分类号： B23K15/002 , B23K15/0093 , B23K15/04 , B23K26/034 , B23K26/28 , B23K2201/001 , B23K2201/06 , B23P15/006 , C21D1/30 , C21D9/50 , C21D9/505 , C21D11/00 , C21D2221/00 , F01D5/063 , F05D2230/233
摘要： PROBLEM TO BE SOLVED: To provide a method for manufacturing a welding rotor attaining enhancement of strength characteristics of a welded area and long useful life in the rotor of a gas turbine engine.
SOLUTION: Two or more of rotor discs 1 are joined to each other by a conventional welding process using a welded part extending in a radial direction relative to a rotor shaft, and thereafter, the welded area is subjected to heat treatment at a predetermined temperature to remove residual tensile stress by stress relaxing. By setting the welded part 3 of the welding rotor of the gas turbine engine to a non-stress relaxing temperature level outstandingly lower than a heat influence area 2 adjacent to the welded part 3, as a result of a large temperature gradient, the residual compression stress or at least substantially reduced residual tensile stress is applied to the welded part.
COPYRIGHT: (C)2010,JPO&INPIT
摘要翻译：要解决的问题：提供一种用于制造焊接转子的方法，其提高燃气轮机的转子中的焊接面积的强度特性和长使用寿命。解决方案：通过使用相对于转子轴在径向方向延伸的焊接部分的常规焊接方法将两个或更多个转子盘1彼此接合，然后，将焊接区域在预定温度以通过应力放松来去除残余拉伸应力。通过将燃气涡轮发动机的焊接转子的焊接部3设定为比与焊接部3相邻的热影响区域2明显低的非应力松弛温度水平，由于温度梯度大，残余压缩对焊接部件施加应力或至少大大降低的残余拉伸应力。版权所有（C）2010，JPO＆INPIT

8. 发明专利

JP2006144789A Method and device for cooling external shroud of gas turbine rotor blade 审中-公开
标题翻译：用于冷却涡轮转子叶片外部风力的方法和装置
公开(公告)号：JP2006144789A
公开(公告)日：2006-06-08
申请号：JP2005328454
申请日：2005-11-14
申请人： Alstom Technology Ltd , Rolls-Royce Deutschland Ltd & Co Kg , アルストムテクノロジーリミテッドALSTOM Technology Ltd , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： JANKE ERIK , HASELBACH FRANK , DR WHITNEY CHRISTOPHER FRANCIS
IPC分类号： F01D5/18 , F01D9/02 , F01D25/24 , F02C7/18
CPC分类号： F01D11/08 , F01D9/04 , F01D25/12 , F05D2240/81 , Y02T50/676
摘要： PROBLEM TO BE SOLVED: To effectively cool a shroud of a rotor blade by supplying cooling air to hit a bottom surface of an external shroud of the rotor blade allover.
SOLUTION: In this cooling method, passive shroud cooling of the rotor blade 5 is accomplished by introducing a plurality of cooling air flows to a hot gas flow upstream of the rotor blade 5. Since angular direction of the cooling air flow is determined at the predetermined radial angle and the predetermined tangential angle based on the aerodynamic and geometric conditions, in the external shroud 6, the cooling air mainly hits the thermally highly loaded bottom surface 11 allover. In the cooling device for executing this cooling method, a cooling air passage 9 to be directed to the hot gas flow is provided in an area of a casing part 3 which protrudes beyond a stator blade 1 in the downstream direction to interrupt transport of the cooling air in the axial direction.
COPYRIGHT: (C)2006,JPO&NCIPI
摘要翻译：要解决的问题：为了有效地冷却转子叶片的护罩，通过供应冷却空气来撞击转子叶片的外护罩的底表面。解决方案：在这种冷却方法中，通过将多个冷却空气流引入转子叶片5上游的热气流来实现转子叶片5的无源护罩冷却。由于冷却空气流的角度方向被确定在预定的径向角度和基于空气动力学和几何条件的预定切向角度下，在外部护罩6中，冷却空气主要撞击热负荷高的底部表面11。在用于执行该冷却方法的冷却装置中，在朝向下游方向突出超过定子叶片1的壳体部分3的区域中设置有指向热气流的冷却空气通道9，以中断冷却空气在轴向。版权所有（C）2006，JPO＆NCIPI

9. 发明专利

JP2014185636A Turbomachine component with erosion resistant and corrosion resistant coating system, and method of manufacturing turbomachine component 审中-公开
标题翻译：具有抗腐蚀和耐腐蚀涂层系统的涡轮机组件及其制造涡轮机组件的方法
公开(公告)号：JP2014185636A
公开(公告)日：2014-10-02
申请号：JP2014027195
申请日：2014-02-17
申请人： Alstom Technology Ltd , アルストムテクノロジーリミテッドALSTOM Technology Ltd , Rolls-Royce Deutschland Ltd & Co Kg , ロールズ−ロイスドイチュラントリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG , Fraunhofer-Ges Zur Foerderung Der Angewandten Forschung Ev , フラウンホーファー−ゲゼルシャフトツルフェルデルングデルアンゲヴァンテンフォルシュングエーファウFraunhofer−Gesellschaft zur Foerderung der angewandten Forschung e.V.
发明人： HANS-JOACHIM KLAM , KAI ORTNER , BJORN ULRICHSOHN
IPC分类号： F04D29/02 , C23C14/06 , C23C30/00 , F01D5/28 , F01D9/02 , F01D25/00 , F02C7/00 , F04D29/38
CPC分类号： F01D5/28 , C23C14/35 , C23C28/00 , C23C28/322 , C23C28/341 , C23C28/347 , C23C28/40 , C23C28/42 , F01D5/288 , F01D9/02 , Y02T50/671
摘要： PROBLEM TO BE SOLVED: To provide a turbomachine component used in a stationary type turbomachine with a coating system, which is easy to apply and flexible in use.SOLUTION: A turbomachine component (10) of a stationary type turbomachine according to the invention comprises: a substrate (16) made of high alloyed 10% to 18% chromium steels or titanium alloys or nickel base alloys or cobalt base alloys and having a substrate surface (19); and an erosion resistant and corrosion resistant coating system (17, 18, 20). The coating system (17, 18, 20) comprises: a first layer (17), which is deposited on the substrate surface (19) of the turbomachine component (10) and acts as a corrosion resistant layer; and a second layer (18), which is deposited on the first layer (17) and acts as an erosion resistant layer. The first layer (17) is a Zr single layer and the second layer (18) is a W/WC multilayer.
摘要翻译：要解决的问题：提供一种具有涂层系统的固定式涡轮机中使用的涡轮机组件，该涂层系统易于应用并且使用灵活。解决方案：根据本发明的固定式涡轮机的涡轮机组件（10）包括：由高合金化的10％至18％铬钢或钛合金或镍基合金或钴基合金制成并具有基底表面（19）的基底（16）; 和耐腐蚀和耐腐蚀的涂层系统（17,18,20）。涂层系统（17,18,20）包括：第一层（17），其沉积在涡轮机组件（10）的基板表面（19）上并用作耐腐蚀层; 和沉积在第一层（17）上并用作抗侵蚀层的第二层（18）。第一层（17）是Zr单层，第二层（18）是W / WC多层。

10. 发明专利

JP2009262320A Method of milling blisk 审中-公开
标题翻译： BLISK的研磨方法
公开(公告)号：JP2009262320A
公开(公告)日：2009-11-12
申请号：JP2009094651
申请日：2009-04-09
申请人： Rolls-Royce Deutschland Ltd & Co Kg , ロールスロイスドイチランドリミテッドウントコンパニーコマンディートゲゼルシャフトRolls−Royce Deutschland Ltd & Co KG
发明人： RIEDEL GREGOR , HOLZE LIANE
IPC分类号： B23C3/18 , B23C5/10 , B23P15/02
CPC分类号： B23P15/006 , B23C3/18 , B23C2215/44 , B23C2220/28 , B23C2220/60 , F01D5/34 , F05D2230/10 , Y10T409/303752
摘要： PROBLEM TO BE SOLVED: To provide a method of milling a blisk for a gas turbine capable of reducing aerodynamic loss. SOLUTION: When blisk blades 13 are formed on a disk blank by milling, the both side surfaces of each blade are finished by a side surface milling. By so milling that cut strips are aligned with the flow direction between the blisk blades, the cut strips of the same width are formed. Consequently, the aerodynamic loss on the negative pressure side 12 and positive pressure side of the blade can be reduced. COPYRIGHT: (C)2010,JPO&INPIT

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