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41. 发明申请

WO2018153796A1 A TURBOMACHINE BLADE OR VANE HAVING A COOLING CHANNEL WITH A CRISS-CROSS ARRANGEMENT OF PINS 审中-公开
公开(公告)号：WO2018153796A1
公开(公告)日：2018-08-30
申请号：PCT/EP2018/053952
申请日：2018-02-16
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： VIANO, Andrea
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/2212
摘要： A turbomachine component having an aerofoil, such as a blade or a vane, is presented. The turbomachine component includes an aerofoil cavity bordered by a suction side wall and a pressure side wall. A cooling channel, for flow of cooling fluid, defined by an internal wall (60) of the cooling channel extends inside the aerofoil cavity. Within the cooling channel, each of the first and the second pins (71, 81) is connected to opposite sides of the internal wall and extends from wall-to-wall. The first and the second pins are non-contiguously and alternatively arranged within the cooling channel and are disposed at an angle, with respect to each other, thereby forming a criss-cross arrangement of the pins. The wall-to-wall extending pins provide greater surface area for heat conduction, generate turbulence in the cooling fluid, and redirect heat from one part of the turbomachine component to another part of the turbomachine component by conduction.

42. 发明申请

WO2018147875A1 SEALING SCHEMES FOR CERAMIC MATRIX COMPOSITE STACKED LAMINATE STRUCTURES 审中-公开
公开(公告)号：WO2018147875A1
公开(公告)日：2018-08-16
申请号：PCT/US2017/017547
申请日：2017-02-10
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： MARRA, John J.
IPC分类号： B32B7/04 , B32B7/08 , B32B18/00 , B32B3/06 , B32B3/08 , B32B3/26 , F01D5/14 , B23P15/04 , F01D5/18 , F01D5/28 , F01D9/04 , F01D9/06
摘要： There is provided a component (10) having a plurality of laminates (12) formed from a ceramic matrix composite material stacked on one another to form a stacked laminate structure (14). A seal (28) formed from a resolidifiable ductile and a thermally conductive metal material (25) is disposed adjacent stacked laminates (12) so as to reduce and/or eliminate air leakage therebetween. The seal (28) comprises a column (48) of the metal material (25) extending through corresponding openings (46) in the laminates (12) between a top end (20) and a bottom end (22) of the stacked laminate structure (14). The metal material (25) comprises an alloy of silver and copper.

43. 发明申请

WO2018141574A1 CMC-TURBINENKOMPONENTE MIT KOMPLEXEN KÜHLSTRUKTUREN SOWIE VERFAHREN ZUR HERSTELLUNG DAZU 审中-公开
公开(公告)号：WO2018141574A1
公开(公告)日：2018-08-09
申请号：PCT/EP2018/051518
申请日：2018-01-23
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： CAMPBELL, Christian Xavier , LAMPENSCHERF, Stefan , PHAM, Gia Khanh , WALTER, Steffen
IPC分类号： B32B18/00 , C04B38/00 , F01D5/18 , F01D5/28 , F01D9/06
摘要： Die Erfindung betrifft nichtmetallische Turbinenkomponente, insbesondere Gasturbinenkomponente, beispielsweise für stationäre Gasturbinen, aus Ceramic Matrix Composite Materialien (CMCs). Durch die vorliegende Erfindung wird erstmals eine CMC-Turbinenkomponente vorgestellt, die über feine und komplexe Kühlkanalstrukturen verfügt. Diese Kühlkanalstrukturen werden innerhalb der CMC-Turbinenkomponente erzeugt, ohne dass diese mechanisch strapazierenden Verfahren wie Ätzen, Fräsen, Schneiden etc. unterworfen wird. Dies ist beispielsweise an den Innenwänden der Kühlkanäle erkennbar.

44. 发明申请

WO2018136042A1 TURBINE ELEMENT 审中-公开
公开(公告)号：WO2018136042A1
公开(公告)日：2018-07-26
申请号：PCT/US2017/013892
申请日：2017-01-18
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： RODRIGUEZ, Jose L. , GOLSEN, Matthew J. , HARRINGTON, John T. , WRIGHT, Stephen , MERRILL, Gary B.
IPC分类号： F01D5/18
摘要： A turbine element for high pressure drop and heat transfer. The turbine element includes a plurality of elements (16) radially placed in columns together aligned in a series of rows of at least four rows across an interior surface of an outer wall of an airfoil (10), creating a pin fin pattern (14) based on the shape of each of the plurality of elements (16), wherein each element (16) includes an inner length between an inner top edge and an inner bottom edge, an inner width between an inner left edge and an inner right edge. The pin fin pattern (14) is highly packed and fills a portion of the interior surface of the outer wall of the airfoil (10).

45. 发明申请

WO2018132629A1 ADAPTIVE MACHINING OF COOLED TURBINE AIRFOIL 审中-公开
公开(公告)号：WO2018132629A1
公开(公告)日：2018-07-19
申请号：PCT/US2018/013435
申请日：2018-01-12
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： ESHAK, Daniel M. , KAMENZKY, Susanne , MILLER, JR., Samuel, R. , VÖHRINGER, Daniel
IPC分类号： F01D5/18
摘要： A method is provided for machining an airfoil section (12) of a turbine blade or vane produced by a casting process. The airfoil section (12) has an outer wall (18) delimiting an airfoil interior having one or more internal cooling passages (28). The method involves: receiving design data pertaining to the airfoil section (12), including a nominal outer airfoil form (40N) and nominal wall thickness (TN) data; generating a machining path by determining a target outer airfoil form (40T), the target outer airfoil form (40T) being generated by adapting the nominal outer airfoil form (40N) such that a nominal wall thickness (TN) is maintained at all points on the outer wall around the one or more internal cooling passages (28) in a subsequently machined airfoil section; and machining an outer surface (18a) of the airfoil section (12) produced by the casting process according to the generated machining path, to remove excess material to conform to the generated target outer airfoil form (40T).

46. 发明申请

WO2018087487A1 PROCÉDÉ DE FABRICATION D'UNE PALE DE TURBOMACHINE 审中-公开
标题翻译：制造涡轮机叶片的方法
公开(公告)号：WO2018087487A1
公开(公告)日：2018-05-17
申请号：PCT/FR2017/053070
申请日：2017-11-10
申请人： SAFRAN HELICOPTER ENGINES
发明人： DANIS, Yann , BOISSELEAU, Denis, Daniel, Jean
IPC分类号： B22F5/04 , F01D5/18 , F01D17/16 , C22C9/06
摘要： L'invention concerne un procédé de fabrication d'une pale (P) de turbomachine du type présentant au moins une cavité 3D (7), caractérisé en ce que ladite pale est réalisée par une succession de dépôts et de consolidations sélectives de couches d'une poudre de fabrication additive métallique à base d'un alliage de cuivre et de nickel, ledit alliage comportant de 2 à 7% de nickel. Elle concerne également une pale de turbomachine, caractérisée en ce qu'elle est fabriquée par fabrication additive métallique en mettant en oeuvre ledit procédé.
摘要翻译：
本发明涉及一种方法用于制造具有至少一个空腔的类型的涡轮机叶片（P） 3D（7），character＆eacute; 其中所述刀片由金属添加剂制造粉末的层的一系列连续缺陷和固结组成; 铜和镍的合金基体，所述合金具有2埃 7％的镍。本发明还涉及一种涡轮机叶片，其特征在于它是通过实施所述方法通过金属添加剂制造而制造的。

47. 发明申请

WO2018075268A1 A POROUS FILM HOLE EXIT AND METHOD FOR MAKING SAME 审中-公开
标题翻译：一种多孔膜孔的出口及其制造方法
公开(公告)号：WO2018075268A1
公开(公告)日：2018-04-26
申请号：PCT/US2017/055584
申请日：2017-10-06
申请人： GENERAL ELECTRIC COMPANY
发明人： BUNKER, Ronald, Scott
IPC分类号： B22F3/105 , B22F5/04 , B22F7/00 , B22F7/08 , F01D5/18
CPC分类号： B22F5/04 , B22F3/1055 , B22F7/004 , B22F7/08 , B28B1/001 , B33Y10/00 , B33Y80/00 , F01D5/183 , F01D5/186 , F01D5/187 , F01D5/28 , F05D2220/32 , F05D2230/10 , F05D2230/22 , F05D2230/31 , F05D2260/202 , Y02P10/295 , Y02T50/676
摘要： A method of forming a cooling hole structure on a turbine component having a component wall with inner and outer surfaces, wherein a cooling hole passes through the component wall and fluidly connects the inner surface and the outer surface. The method includes the steps of forming a recess communicating with the hole and the outer surface; and using an additive manufacturing process to form a porous structure in the recess.
摘要翻译：一种在具有带有内表面和外表面的部件壁的涡轮机部件上形成冷却孔结构的方法，其中冷却孔穿过部件壁并流体地连接内表面和外表面。该方法包括以下步骤：形成与孔和外表面连通的凹部; 并使用增材制造工艺在凹槽中形成多孔结构。

48. 发明申请

WO2018031032A1 BLADE FOR GAS TURBINE ENGINE 审中-公开
标题翻译：燃气涡轮发动机叶片
公开(公告)号：WO2018031032A1
公开(公告)日：2018-02-15
申请号：PCT/US2016/046778
申请日：2016-08-12
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： CARRIER, Gilles
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/141 , F01D5/147 , F01D5/187 , F05D2230/21 , F05D2230/50 , F05D2240/304 , F05D2260/22141 , F05D2260/941
摘要： Airfoil outer wall thickness of a gas turbine engine blade is initially increased in a zone that is proximate the trailing edge and blade hub greater than comparable greatest wall thickness anywhere else along the trailing edge from outboard that zone all the way to the blade tip. The initially increased thickness zone (50) includes a transition zone (Lx) that bridges the respective airfoil outer wall thicknesses (50) proximate the hub end (42) and tip (44) of the blade (20). The initially increased outer wall thickness is then reduced to a final decreased outer wall thickness post casting. Some embodiments also incorporate pedestals (52) with compound curve fillets in the increased wall thickness zone.
摘要翻译：燃气涡轮发动机叶片的翼型外壁厚度最初在接近后缘和叶片毂的区域中增加大于沿着后缘的任何其他地方从该区域外侧的可比较的最大壁厚全部通往刀尖的路。最初增加的厚度区域（50）包括桥接叶片（20）的毂端（42）和尖端（44）附近的相应翼型外壁厚度（50）的过渡区域（Lx）。最初增加的外壁厚度然后减小到铸造后的最终减小的外壁厚度。一些实施例还在增大的壁厚区域中结合具有复合曲线圆角的基座（52）。

49. 发明申请

WO2018017172A3 CERAMIC MATRIX COMPOSITE AIRFOIL COOLING 审中-公开
公开(公告)号：WO2018017172A3
公开(公告)日：2018-01-25
申请号：PCT/US2017/030006
申请日：2017-04-28
申请人： GENERAL ELECTRIC COMPANY
发明人： GALLIER, Kirk, Douglas , SENILE, Darrell, Glenn , CALHOUN, John
IPC分类号： F01D5/18 , F01D5/28
摘要： Airfoils for gas turbine engines are provided. In one embodiment, an airfoil formed from a ceramic matrix composite material includes opposite pressure and suction sides extending radially along a span and defining an outer surface of the airfoil. The airfoil also includes opposite leading and trailing edges extending radially along the span. The pressure and suction sides extend axial I v between the leading and trailing edges. The leading edge defines a forward end of the airfoil, and the trailing edge defining an aft end of the airfoil. Further, the airfoil includes a trailing edge portion defined adjacent the trailing edge at the aft end of the airfoil; a plenum defined within the airfoil forward of the training edge portion; and a cooling passage defined within the trailing edge portion proximate the suction side. Methods for forming airfoils for gas turbine engines also are provided.

50. 发明申请

WO2017196698A1 AIRFOIL HAVING A SKIN COOLING CIRCUIT 审中-公开
标题翻译：具有皮肤冷却回路的机翼
公开(公告)号：WO2017196698A1
公开(公告)日：2017-11-16
申请号：PCT/US2017/031494
申请日：2017-05-08
申请人： GENERAL ELECTRIC COMPANY
发明人： BUNKER, Ronald, Scott
IPC分类号： F01D5/18 , F01D5/28
摘要： An airfoil for a turbine engine having an engine component including an internal cooling circuit fluidly coupled to a plurality of passages within the outer wall of the engine component where cooling air moves from the internal cooling circuit to an outer surface of the engine component through the passages.
摘要翻译：用于涡轮发动机的翼型件具有发动机部件，该发动机部件包括内部冷却回路，该内部冷却回路流体地联接到发动机部件的外壁内的多个通道，其中冷却空气从内部冷却回路移动到外部发动机部件的表面通过通道。

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