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1. 发明公开

EP3179037A1 RIBLETS FOR THE BLADE OF A GAS TURBINE ENGINE 审中-公开
标题翻译：燃气涡轮发动机叶片的叶片
公开(公告)号：EP3179037A1
公开(公告)日：2017-06-14
申请号：EP16201373.4
申请日：2016-11-30
申请人： General Electric Company
发明人： BERSCHBACK, Casey Lauren , WOOD, Trevor Howard , LIN, Wendy Wenling , LIOU, Lara
IPC分类号： F01D5/14 , F01D9/04
CPC分类号： F04D29/388 , F01D5/141 , F01D9/04 , F01D9/041 , F02C3/04 , F04D29/023 , F04D29/325 , F04D29/542 , F05D2220/32 , F05D2220/36 , F05D2230/23 , F05D2240/35 , F05D2250/18 , F05D2250/181 , F05D2250/182 , F05D2250/61 , F05D2260/95 , F05D2300/501 , Y02T50/672 , Y02T50/673
摘要： An airfoil 90 of a propulsion device having a first riblet laminate 136 with a first adhesive layer 156 on at least a first portion of the airfoil surface 92 and a first riblet array sheet 130 disposed on at least a portion of the first adhesive layer 156. The first riblet array sheet 130 defines a first plurality of contiguous geometric features 110 having rigid peaks 146 and valleys 148 extending in a first rib direction. The first plurality of contiguous geometric features 110 define a total width to total height ratio W:H of about 1:1 to about 2.5:1 with a maximum total height of about 0.65 mm or less. A second riblet array laminate 132 is also disclosed in an embodiment.
摘要翻译：推进装置的翼型件90具有第一肋状层压件136，第一肋状件层叠件136具有在翼型表面92的至少第一部分上的第一粘合剂层156和设置在第一粘合剂层156的至少一部分上的第一肋状阵列片130。第一肋状阵列片130限定第一多个连续几何特征110，其具有在第一肋方向上延伸的刚性峰146和谷148。第一多个连续几何特征110限定约1：1至约2.5：1的总宽度与总高度比W:H，最大总高度为约0.65mm或更小。在一个实施例中还公开了第二肋状阵列层压件132。

2. 发明公开

EP3059397A4 SHAFT SEAL DEVICE, ROTARY MACHINE, AND METHOD FOR MANUFACTURING SHAFT SEAL DEVICE 审中-公开
标题翻译：轴封装置，旋转机械及其制造方法的轴封装置
公开(公告)号：EP3059397A4
公开(公告)日：2017-01-04
申请号：EP14863444
申请日：2014-11-10
申请人： MITSUBISHI HEAVY IND LTD
发明人： YOSHIDA AZUMI , UEHARA HIDEKAZU , OZAKI KOHEI , NISHIMOTO SHIN
IPC分类号： F16J15/3292 , F01D11/00
CPC分类号： F01D11/00 , F01D11/001 , F05D2220/32 , F05D2240/57 , F05D2240/59 , F05D2240/60 , F05D2250/181 , F05D2250/182 , F05D2250/184 , F05D2250/241 , F05D2250/28 , F05D2250/711 , F05D2250/712 , F16J15/3292
摘要： A shaft sealing device (10) includes a plurality of leaves (20) that is arranged in a periphery of a rotating shaft (50) and divides a space around the rotating shaft into two spaces in an axial direction of the rotating shaft, and a side seal plate that is arranged on one side of the leaf in the axial direction and has an opposite surface facing a side end on one side of the leaf. The leaf and/or the side seal plate has a friction reducing portion for reducing a friction force between the opposite surface and a surface of the side end.

3. 发明公开

EP3019723A1 PLATED POLYMER COMPRESSOR 审中-公开
标题翻译：涂层的聚合物压缩机
公开(公告)号：EP3019723A1
公开(公告)日：2016-05-18
申请号：EP14823763.9
申请日：2014-07-09
申请人： United Technologies Corporation
发明人： ROACH, James T. , WATSON, Charles R. , COOK, Grant O. , BARNETT, Barry , BUGAJ, Shari J. , LEVASSEUR, Glenn
IPC分类号： F02C7/00 , F02C7/30 , F01D25/24 , F01D5/12 , F01D5/28 , F04D29/40 , F04D29/38 , C25D5/56 , C25D1/02 , B05D1/00
CPC分类号： F04D29/023 , B64D33/06 , B64D2033/0206 , C23C18/1605 , C23C18/1641 , C23C18/1651 , C23C18/1653 , C25D5/022 , C25D5/10 , C25D5/12 , C25D5/16 , C25D5/56 , F01D5/282 , F01D5/288 , F01D5/3092 , F01D5/34 , F01D25/005 , F01D25/02 , F04D29/322 , F04D29/324 , F04D29/522 , F04D29/542 , F05D2220/36 , F05D2250/181 , F05D2250/182 , F05D2250/61 , F05D2300/10 , F05D2300/43 , F05D2300/512 , F05D2300/611 , Y02T50/672 , Y02T50/673
摘要： Plated polymeric gas turbine engine parts and methods for fabricating lightweight plated polymeric gas turbine engine parts are disclosed. The parts include a polymeric substrate plated with one or more metal layers. The polymeric material of the polymeric substrate may be structurally reinforced with materials that may include carbon, metal, or glass. The polymeric substrate may also include a plurality of layers to form a composite layup structure.

4. 发明授权

EP2087207B1 TURBINENSCHAUFEL 有权
标题翻译：涡轮叶片
公开(公告)号：EP2087207B1
公开(公告)日：2016-04-20
申请号：EP07821492.1
申请日：2007-10-18
申请人： Siemens Aktiengesellschaft
发明人： GROSS, Heinz-Jürgen
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/187 , F01D5/147 , F05D2250/181 , F05D2250/28 , F05D2250/34 , F05D2250/70 , F05D2260/22141

5. 发明公开

EP2094964A4 WALL OF A ROCKET ENGINE 审中-公开
标题翻译： WALL在火箭发动机
公开(公告)号：EP2094964A4
公开(公告)日：2013-05-01
申请号：EP06835868
申请日：2006-12-19
申请人： VOLVO AERO CORP
发明人： BOMAN ARNE
IPC分类号： F02K9/64 , F02K9/97
CPC分类号： F02K9/64 , F02K9/972 , F05D2230/00 , F05D2250/18 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/28 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141

6. 发明授权

EP2226486B1 Verfahren zur Herstellung eines Ejektor-Düsen-Rohrs 有权
标题翻译：一种用于喷射器的喷嘴管的制备方法
公开(公告)号：EP2226486B1
公开(公告)日：2011-06-29
申请号：EP09011065.1
申请日：2009-08-28
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Todorovic, Predrag
IPC分类号： F02K1/36 , B64D33/10
CPC分类号： F02K1/36 , B21D51/06 , B21D51/10 , B21D53/06 , B64D33/10 , F01D25/12 , F01D25/18 , F05D2250/18 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2260/20 , F05D2260/601 , Y02T50/675 , Y10T29/49366 , Y10T29/49401 , Y10T29/49428 , Y10T29/49432

7. 发明公开

EP2267275A2 A shroudless blade 审中-公开
标题翻译： Schaufel ohne甲板
公开(公告)号：EP2267275A2
公开(公告)日：2010-12-29
申请号：EP10165915.9
申请日：2010-06-15
申请人： Rolls-Royce plc
发明人： Harvey, Neil , Baralon, Stephan
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/20 , F01D21/045 , F04D29/164 , F04D29/34 , F04D29/682 , F04D29/684 , F05D2240/307 , F05D2250/181 , F05D2250/182 , Y02T50/673
摘要： A shroudless blade 2 for use in a compressor or fan of an axial flow gas turbine engine includes a treatment to the tips 10 of the blades 2 to improve the surge margin of the compressor. A series of cross bleed holes 22 are formed at the tip of the blade, which may be a stator or rotor component, extending between the pressure 8 and suction 6 sides of the blades. Notches are provided at the tip of the blades to provide initiation sites for any fatigue cracks such that the cracks propagate from the base of these slots or notches 36 and radially inwards into the body of the blades 2. The present invention provides an arrangement which by provision of the cross bleed holes the propagation of the cracks is arrested. A preferred placement and orientation for the holes 22 for best mechanical and aerodynamic performance is described.
摘要翻译：用于轴流式燃气涡轮发动机的压缩机或风扇的无挡板叶片2包括对叶片2的尖端10的处理，以改善压缩机的浪涌裕度。在叶片的尖端处形成一系列交叉排放孔22，其可以是在叶片的压力8和吸力6侧之间延伸的定子或转子部件。在叶片的尖端处设置切口以提供任何疲劳裂纹的起始位置，使得裂纹从这些槽或凹槽36的基部传播并径向向内进入叶片2的本体。本发明提供了一种布置，其通过提供交叉泄漏孔裂缝的传播被阻止。描述了用于最佳机械和空气动力学性能的孔22的优选布置和取向。

8. 发明公开

EP2122183A1 A DIFFUSER FOR DECELERATING A COMPRESSED FLUID 审中-公开
标题翻译：扰流板来减速压缩流体
公开(公告)号：EP2122183A1
公开(公告)日：2009-11-25
申请号：EP08708164.2
申请日：2008-01-24
申请人： Siemens Aktiengesellschaft
发明人： TWELL, Philip
IPC分类号： F04D29/54 , F01D9/04
CPC分类号： F04D29/541 , F01D9/041 , F01D9/042 , F05D2250/11 , F05D2250/18 , F05D2250/181 , F05D2250/182 , F05D2250/324 , F05D2250/70 , F05D2260/36
摘要： A diffuser for decelerating a compressed gas, is provided, which includes a ring divided at circumferential positions around the ring into several arcuate sections, the complete ring being assembled from these sections. The ring defines one or more passages, the cross-section of which increases in the direction of travel of a fluid through the diffuser. The interface between adjacent sections is configured in a manner preventing relative movement between the sections. The interface may be configured to have a series of interlocking serrations along the axial length of the diffuser. In a preferred embodiment, there are two arcuate sections involving two interfaces, and the peaks and troughs of the serrations are arranged at an angle to a longitudinal axis of the diffuser. Good immunity to relative movement between the sections is achieved when this angle is of opposite sign at the two interfaces.

9. 发明公开

EP2094964A1 WALL OF A ROCKET ENGINE 审中-公开
标题翻译： WALL在火箭发动机
公开(公告)号：EP2094964A1
公开(公告)日：2009-09-02
申请号：EP06835868.8
申请日：2006-12-19
申请人： Volvo Aero Corporation
发明人： BOMAN, Arne
IPC分类号： F02K9/64 , F02K9/97
CPC分类号： F02K9/64 , F02K9/972 , F05D2230/00 , F05D2250/18 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2250/28 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141
摘要： A wall (2) configured to withstand a high thermal load, said wall (2) having a surface that is turned away from a heat source and provided with at least one strengthening element (7, 12, 17, 22, 27, 29) that, from a base portion thereof, protrudes from said surface. Said at least one strengthening element (7, 12, 17, 22, 27, 29) presents a decreasing width from its base portion (8, 13, 18, 23, 28, 32) towards a top portion (9, 14, 19, 24, 33) there of. The wall being an engine wall of a thrust nozzle of a rocket engine.

10. 发明授权

EP2616642B1 TURBINE COMPONENT WITH MULTI-SCALE TURBULATION FEATURES 有权
标题翻译：具有多级涡轮特征的涡轮部件
公开(公告)号：EP2616642B1
公开(公告)日：2018-05-16
申请号：EP11776612.1
申请日：2011-09-08
申请人： Siemens Energy, Inc.
发明人： LEE, Ching-Pang , JIANG, Nan , MARRA, John J. , RUDOLPH, Ronald J.
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2250/181 , F05D2250/60 , F05D2250/611 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.

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