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41. 发明公开

EP2494154A4 GAS TURBINE ENGINE COMPONENT 有权转让
标题翻译： GASTURBINENMOTORKOMPONENTE
公开(公告)号：EP2494154A4
公开(公告)日：2014-09-03
申请号：EP09850930
申请日：2009-10-27
申请人： GKN AEROSPACE SWEDEN AB
发明人： SAMUELSSON RICKARD , REIMERS ROBERT
IPC分类号： F01D9/04 , F01D5/30
CPC分类号： F01D9/042 , F05B2260/301 , F05D2230/18 , F05D2240/12 , F05D2260/31 , F05D2260/37 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： A gas turbine engine component includes a ring element and a plurality of circumferentially spaced load carrying vanes extending in a radial direction of the ring element. At least one of the vanes is made of a composite material. The at least one composite vane is fastened to the ring element. The component further includes first and second wall portions that are fixed in relation to the ring element and arranged on opposite sides of the composite vane. At least a first hole extends through the first wall portion, the composite vane and the second wall portion. The first hole is adapted to receive a first insertion member. The component is arranged such as to, with regard to the first hole, provide a tight fit for the first insertion member in the first wall portion as well as in the composite vane and to provide a loose fit with a radial play in the second wall portion.
摘要翻译：燃气涡轮发动机部件包括环形元件和沿环形元件的径向方向延伸的多个周向间隔开的承载叶片。至少一个叶片由复合材料制成。至少一个复合叶片紧固到环形元件。该部件还包括相对于环形元件固定并布置在复合叶片的相对侧上的第一和第二壁部分。至少第一孔延伸穿过第一壁部分，复合叶片和第二壁部分。第一孔适于接收第一插入构件。该部件布置成就第一孔而言，为第一插入构件在第一壁部分和复合叶片中提供紧密配合，并且提供与第二壁中的径向游隙的松配合一部分。

42. 发明授权

KR101823703B1 진공 펌프 有权
标题翻译：真空泵
公开(公告)号：KR101823703B1
公开(公告)日：2018-03-14
申请号：KR1020127017197
申请日：2011-05-20
申请人： 에드워즈 가부시키가이샤
发明人： 가바사와다카시
IPC分类号： F04D19/04 , F04D29/02 , F04D25/16
CPC分类号： F04D19/042 , F04D17/168 , F04D19/044 , F04D29/023 , F05D2230/14 , F05D2230/18 , F05D2230/90 , F05D2260/37 , F05D2300/121 , F05D2300/43 , F05D2300/516 , F05D2300/603 , F05D2300/6034
摘要： 섬유강화플라스틱재를원통형으로성형하여원통로터를사용한경우에도, 원통로터의성형후에마무리가공을행하지않아도되는진공펌프를제공한다. 터보분자펌프부(14)와나사홈 펌프부(15)를가지며, 터보분자펌프부(14)의로터(17)의하단부에나사홈 펌프부(15)의섬유강화플라스틱재를원통형으로성형하여이루어지는원통로터(21)의상단부를접합한진공펌프에있어서, 터보분자펌프부(14)의로터(17)와나사홈 펌프부(15)의원통로터(21)의접합부분을배기경로(24)의상류측에설치한다. 이로인해, 원통로터(21)의성형후에마무리가공을행하지않아도된다. 또한, 원통로터(21)의성형후에마무리가공을행하는경우는, 원통로터(21)의요철부분에수지를코팅하거나, 권부각을 45도이하로하여헬리컬형상으로섬유를감아도된다.
摘要翻译：本发明提供一种真空泵，即使在将纤维增强塑料成形为圆筒状的情况下使用圆筒状的转子的情况下，也能够在形成圆筒状的转子后不需要精加工。在涡轮分子泵单元14的转子17的下端形成筒状的分子泵单元14和螺旋槽泵单元15，螺纹槽泵单元15的纤维增强塑料材料形成为圆筒状涡轮分子泵单元14的转子17与螺旋槽泵单元15的源通道21的连接部连接到排气通道24 ）它安装在上游侧。结果，在形成圆柱形转子21之后可能不执行精加工工艺。当成形后圆柱形转子21完成时，可以将树脂涂覆在圆柱形转子21的凹凸部分上，或者可以将纤维以45°或更小的缠绕角度卷绕成螺旋形状。

43. 发明公开

KR1020130093463A 진공 펌프 审中-实审
标题翻译：真空泵
公开(公告)号：KR1020130093463A
公开(公告)日：2013-08-22
申请号：KR1020127017197
申请日：2011-05-20
申请人： 에드워즈 가부시키가이샤
发明人： 가바사와다카시
IPC分类号： F04D19/04 , F04D29/02 , F04D25/16
CPC分类号： F04D19/042 , F04D17/168 , F04D19/044 , F04D29/023 , F05D2230/14 , F05D2230/18 , F05D2230/90 , F05D2260/37 , F05D2300/121 , F05D2300/43 , F05D2300/516 , F05D2300/603 , F05D2300/6034
摘要： 섬유 강화 플라스틱재를 원통형으로 성형하여 원통 로터를 사용한 경우에도, 원통 로터의 성형 후에 마무리 가공을 행하지 않아도 되는 진공 펌프를 제공한다. 터보 분자 펌프부(14)와 나사 홈 펌프부(15)를 가지며, 터보 분자 펌프부(14)의 로터(17)의 하단부에 나사 홈 펌프부(15)의 섬유 강화 플라스틱재를 원통형으로 성형하여 이루어지는 원통 로터(21)의 상단부를 접합한 진공 펌프에 있어서, 터보 분자 펌프부(14)의 로터(17)와 나사 홈 펌프부(15)의 원통 로터(21)의 접합 부분을 배기 경로(24)의 상류측에 설치한다. 이로 인해, 원통 로터(21)의 성형 후에 마무리 가공을 행하지 않아도 된다. 또한, 원통 로터(21)의 성형 후에 마무리 가공을 행하는 경우는, 원통 로터(21)의 요철 부분에 수지를 코팅하거나, 권부각을 45도 이하로 하여 헬리컬 형상으로 섬유를 감아도 된다.
摘要翻译：提供一种真空泵，其中即使使用通过将纤维增强塑料材料成形为圆柱形而获得的圆柱形转子，也不需要在圆筒形转子成形之后进行精加工。真空泵具有涡轮分子泵部分和螺纹槽泵部分。通过将螺纹槽泵部的纤维强化塑料成型为圆筒状而得到的圆筒状转子的上端部与涡轮分子泵部的转子的下端部接合。涡轮分子泵部的转子和螺纹槽泵部的圆筒形转子的接合部设置在排气通路的上游。结果，在圆柱形转子成形之后不需要执行精加工。如果在圆柱形转子成形之后执行精加工，则可以将树脂涂覆在圆柱形转子的凹凸部分上，或者纤维可以以不大于45度的卷绕角螺旋缠绕。

44. 发明授权

EP2960008B1 ROTOR BLADE MANUFACTURE 有权
标题翻译：旋转叶片的生产
公开(公告)号：EP2960008B1
公开(公告)日：2016-08-24
申请号：EP15169812.3
申请日：2015-05-29
申请人： Rolls-Royce plc
发明人： Raven, Gemma , Taylor, Christopher , May, Alexander , Baird, Andrew
IPC分类号： B23P6/00 , B24B19/14 , F01D5/30 , F01D5/28
CPC分类号： F01D5/141 , B23P6/002 , B24B19/14 , F01D5/027 , F01D5/20 , F01D5/3038 , F01D25/285 , F04D29/322 , F04D29/644 , F05D2220/32 , F05D2230/10 , F05D2230/18 , F05D2230/60 , F05D2230/64 , F05D2240/30 , F05D2240/307 , Y10T29/49323
摘要： A method is provided of processing one or more blades (500) of a row of blades (500) which forms part of a rotor for a gas turbine engine. The method includes: providing a rotor disc (504) having a slot (502) for mounting one or more blades (500); loading the blades (500) in the slot (502) and loading the wax blocks (506) in or adjacent the slot (502), the wax blocks (506) being configured and positioned such that, on loading, the blades (500) shear material from the wax blocks (506), the sheared wax blocks (506) reducing a range of tilt angles which can be adopted by the blades (500); and performing a processing operation on the loaded blades (500).

45. 发明公开

EP2816430A1 Method of finishing a blade 有权转让
标题翻译： Verfahren zur Endbearbeitung einer Klinge
公开(公告)号：EP2816430A1
公开(公告)日：2014-12-24
申请号：EP14171908.8
申请日：2014-06-11
申请人： Rolls-Royce plc
发明人： Hanlon, Roisin
IPC分类号： G05B19/42
CPC分类号： F01D5/147 , F01D9/02 , F05D2230/18 , G05B19/401 , G05B2219/37365 , G05B2219/37569 , G05B2219/37571 , G05B2219/45147 , G05B2219/50067 , G05B2219/50207 , Y10T29/49336
摘要： An automated technique for finishing gas turbine engine blades or vanes by generating a bespoke tooling path for each blade or vane. The bespoke tooling path is generated by scanning the aerofoil surface to generate a 3-D electronic representation of the surface. The 3-D electronic surface is then analysed to identify imperfections or defects, and then a machining path a generated through which the imperfections can be removed. The machining path is determined so as to smoothly blend the surface back to the underlying surface where the imperfections had been present. In this way, the resulting aerofoil, once machined, has optimized aerodynamic performance.
摘要翻译：一种用于通过为每个叶片或叶片产生定制的工具路径来完成燃气涡轮发动机叶片或叶片的自动化技术。定制的工具路径是通过扫描机翼表面产生表面的3-D电子表示来产生的。然后分析3-D电子表面以识别缺陷或缺陷，然后识别产生的缺陷的加工路径a。确定加工路径以使表面平滑地混合到存在缺陷的下面的表面上。以这种方式，所得到的机翼一旦被加工，已经优化了空气动力性能。

46. 发明公开

EP2494154A1 GAS TURBINE ENGINE COMPONENT 有权转让
标题翻译：燃气轮机部件
公开(公告)号：EP2494154A1
公开(公告)日：2012-09-05
申请号：EP09850930.0
申请日：2009-10-27
申请人： Volvo Aero Corporation
发明人： SAMUELSSON, Rickard , REIMERS, Robert
IPC分类号： F01D9/04 , F01D5/30
CPC分类号： F01D9/042 , F05B2260/301 , F05D2230/18 , F05D2240/12 , F05D2260/31 , F05D2260/37 , F05D2300/603 , Y02T50/672 , Y02T50/673
摘要： The invention concerns a gas turbine engine component (15), comprising: a ring element (14, 27) and a plurality of circumferentially spaced load carrying vanes (12) extending in a radial direction of the ring element (14, 27); wherein at least one of said vanes (12) is made of a composite material, and wherein the at least one composite vane (12) is fastened to the ring element (14, 27), said component (15) further comprising: first and second wall portions (20, 32) that are fixed in relation to the ring element (14, 27) and arranged on opposite sides of the composite vane (12); and at least a first hole (61) extending through the first wall portion (20), the composite vane (12) and the second wall portion (32), wherein said first hole (61) is adapted to receive a first insertion member (63). The invention is characterized in that the component (15) is arranged such as to, with regard to the first hole (61), provide a tight fit (65a, 65b) for the first insertion member (63) in the first wall portion (20) as well as in the composite vane (12) and to provide a loose fit (66) with a radial play in the second wall portion (32). The invention also concerns a gas turbine component comprising a component of the above type.

47. 发明授权

EP2956644B1 GAS TURBINE ENGINE COMPONENT HAVING SURFACE INDICATOR 有权转让
公开(公告)号：EP2956644B1
公开(公告)日：2018-10-03
申请号：EP13875227.4
申请日：2013-02-14
申请人： United Technologies Corporation
发明人： PROPHETER-HINCKLEY, Tracy, A. , THOMAS, Peter Holman
IPC分类号： F02C7/00 , F02C9/00 , F02C7/12 , F01D5/18 , F01D25/12 , F02K3/00 , B22C9/10
CPC分类号： F01D5/185 , B22C9/103 , B22C9/108 , F01D5/005 , F01D5/186 , F01D5/187 , F05D2230/18 , F05D2260/204 , F05D2260/80 , G01M15/14
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a body portion, a cooling circuit disposed within the body portion and including at least a first cavity, a core in fluid communication with the first cavity, and an exit surface that extends through an exterior surface of the body portion. At least one surface indicator is visible near the exit surface.

48. 发明公开

EP2587069A4 VACUUM PUMP 有权
公开(公告)号：EP2587069A4
公开(公告)日：2017-10-18
申请号：EP11797957
申请日：2011-05-20
申请人： EDWARDS JAPAN LTD
发明人： KABASAWA TAKASHI
IPC分类号： F04D19/04 , F04D17/16 , F04D29/02
CPC分类号： F04D19/042 , F04D17/168 , F04D19/044 , F04D29/023 , F05D2230/14 , F05D2230/18 , F05D2230/90 , F05D2260/37 , F05D2300/121 , F05D2300/43 , F05D2300/516 , F05D2300/603 , F05D2300/6034
摘要： Provided is a vacuum pump in which no finish processing has to be carried out after shaping of a cylindrical rotor even in use of a cylindrical rotor obtained by shaping a fiber-reinforced plastic material into a cylindrical shape. The vacuum pump has a turbo-molecular pump section and a thread groove pump section. The upper end section of a cylindrical rotor, which is obtained by shaping a fiber-reinforced plastic material into a cylindrical shape, of the thread groove pump section, is joined to the lower end section of a rotor of the turbo-molecular pump section. A joining portion of the rotor of the turbo-molecular pump section and the cylindrical rotor of the thread groove pump section is disposed upstream of an exhaust passage. As a result, finish processing does not have to be carried out after shaping of the cylindrical rotor. If finish processing is performed after shaping of the cylindrical rotor a resin may be coated onto a rugged portion of the cylindrical rotor, or fibers may be helically wound at a winding angle not greater than 45 degrees.

49. 发明公开

EP3203032A1 METHOD OF CALCULATION OF THE THROAT AREA FOR A VANE OF A GAS TURBINE ENGINE AND OF MODYFING THE VANES 有权转让
标题翻译：计算燃气涡轮发动机叶片喉部面积并模拟烟道的方法
公开(公告)号：EP3203032A1
公开(公告)日：2017-08-09
申请号：EP17154476.0
申请日：2017-02-02
申请人： United Technologies Corporation
发明人： CHUONG, Conway
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F05D2220/323 , F05D2230/10 , F05D2230/12 , F05D2230/18 , F05D2240/122 , F05D2260/81
摘要： A method of calculating a throat area (66) of a section of a machinery includes outlining a boundary (68) of the throat area (66) of the section, selecting a plurality of inspection points (OD1-N, ID1-N, SS1-N, PS1-N) along the boundary (68) of the throat area (66), dividing the throat area (66) into a plurality of sections (S1-S8), calculating an individual area of each of the plurality of sections (S1-S8) and summing the individual areas of each of the plurality of sections (S1-S8) to calculate the throat area (66).
摘要翻译：计算机器的一部分的喉部区域（66）的方法包括概述该部分的喉部区域（66）的边界（68），选择多个检查点（OD1-N，ID1-N，SS1 （66）的边界（68），将喉部区域（66）分成多个部分（S1-S8），计算多个部分中的每一个的单独区域（S1-S8）并且对所述多个部分中的每个部分（S1-S8）的各个区域进行求和以计算咽喉区域（66）。

50. 发明公开

EP3069821A3 VERFAHREN ZUR FERTIGUNG EINES BAUTEILS 审中-公开
标题翻译： VERFAHREN ZUR FERTIGUNG EINES BAUTIILS
公开(公告)号：EP3069821A3
公开(公告)日：2016-10-19
申请号：EP16151277.7
申请日：2016-01-14
申请人： MTU Aero Engines AG
发明人： Göpfert, Dagobert
IPC分类号： B24B31/06 , B22F3/105 , B22F3/24 , B22F7/08 , G02B23/24 , C23C24/04 , F01D5/28 , B24B31/00 , F01D21/00 , F01D25/00 , G01N21/64 , A61B1/00
CPC分类号： F01D25/24 , A61B1/0011 , B22F1/0059 , B22F1/0074 , B22F3/1055 , B22F5/009 , B22F2999/00 , B24B31/00 , C23C24/04 , F01D5/284 , F01D5/286 , F01D21/003 , F01D25/005 , F05D2230/18 , F05D2230/22 , F05D2230/31 , F05D2230/90 , F05D2240/00 , F05D2250/62 , F05D2250/621 , F05D2260/80 , F05D2260/83 , G01N21/91 , G02B23/2476 , Y02P10/295 , B22F2003/247 , B22F2203/03 , B22F2202/01
摘要： Die Erfindung betrifft ein Verfahren zur Fertigung eines Bauteils, insbesondere eines Bauteils einer Strömungsmaschine, umfassend zumindest folgende Verfahrensschritte: a) Herstellung eines Rohlings des Bauteils mittels einem additiven Herstellungsverfahren oder Aufbringen mindestens eines ersten Bauteilelements auf ein zweites Bauteilelement mittels mindestens einem additiven Herstellungsverfahren zur Herstellung eines Rohlings des Bauteils; b) Einstellen einer vordefinierten Rauheit und/oder Güte von zumindest einem Teilbereich einer Oberfläche des Rohlings mittels Gleitschleifen; und c) Zerstörungsfreie Prüfung von zumindest dem Teilbereich der Oberfläche des Rohlings mit vordefinierter Rauheit und/oder Güte mittels einer Eindringprüfung, nämlich einer fluoreszierenden Eindringprüfung oder Farbeindringprüfung. Die Erfindung betrifft weiterhin die Verwendung des Verfahrens sowie Bauteile, die mit dem Verfahren hergestellt werden.
摘要翻译：公开了一种用于生产组分，特别是涡轮机组件的方法。在一个实施方案中，该方法包括以下工艺步骤：a）通过添加剂生产工艺或通过至少一种用于生产空白的添加剂生产方法在第二组分元素上沉积至少第一组分元素来生产组分的坯料的组件; b）通过振动研磨来设定坯料表面的至少一个部分的预定粗糙度和/或质量; 以及c）通过穿透试验，特别是荧光渗透试验或染料渗透试验，至少对具有预定粗糙度和/或质量的坯料表面的部分进行非破坏性试验。还公开了使用该方法以及使用该方法生产的组件的用途。

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