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1. 发明授权

EP3098515B1 JET ENGINE, FLYING BODY, AND METHOD FOR OPERATING A JET ENGINE 有权
公开(公告)号：EP3098515B1
公开(公告)日：2018-12-26
申请号：EP15768566.0
申请日：2015-02-17
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： UENO, Yoshihiko , FURUYA, Shojiro
IPC分类号： F23R3/28 , F02K7/10 , F02K7/18
CPC分类号： F23R3/28 , F02K7/10 , F02K7/18 , F05D2220/80 , F05D2250/184 , F05D2250/313 , F05D2260/99 , F23R2900/00014 , Y02T50/671
摘要： A jet engine includes an inlet and a combustor. the inlet takes in air. The combustor combusts fuel with the air. The combustor (12) includes an injector (20) having a plurality of openings (31a, 31b) from which the fuel is injected. The plurality of openings (31a, 31b) are arranged in a direction perpendicular to a direction of a flow path of the air in the combustor (12). The plurality of openings (31a, 31b) include two types of openings different in area.

2. 发明授权

EP2494210B1 MACHINE WITH ABRADABLE RIDGES AND METHOD 有权
公开(公告)号：EP2494210B1
公开(公告)日：2018-09-26
申请号：EP10771600.3
申请日：2010-10-12
申请人： Nuovo Pignone S.p.A.
发明人： GIOVANNETTI, Lacopo , MICHELASSI, Vittorio , GIANNOZZI, Massimo , GHASRIPOOR, Farshad , GRAY, Dennis, M. , SHENG, Nuo
IPC分类号： F04D29/02 , F04D29/16 , F04D29/44 , F01D11/12
CPC分类号： F04D29/023 , F01D11/122 , F04D29/162 , F04D29/441 , F05D2250/181 , F05D2250/182 , F05D2250/183 , F05D2250/184 , F05D2300/17 , F05D2300/173 , F05D2300/43 , F05D2300/432 , F05D2300/434
摘要： A machine having a fixed part including a portion with a smooth surface is provided. The machine also includes a rotating part configured to rotate relative to the fixed part, the rotating part directly facing the portion of the fixed part, and plural ridges formed on the portion of the fixed part directly facing the rotating part, the plural ridges comprising an abradable material, wherein the abradable material is configured to be inoperable at temperatures above about 1000° C.

3. 发明公开

EP3249267A4 SEAL DEVICE FOR TURBINE, TURBINE, AND THIN PLATE FOR SEAL DEVICE 有权转让
公开(公告)号：EP3249267A4
公开(公告)日：2018-03-14
申请号：EP15882747
申请日：2015-12-22
申请人： MITSUBISHI HITACHI POWER SYS
发明人： YOSHIDA AZUMI , UEHARA HIDEKAZU , OYAMA HIROHARU , OZAKI KOHEI , HAMADA KATSUHISA , SUGISHITA HIDEAKI , NISHIKAWA TOYOHARU , KUWAMURA YOSHIHIRO , HATANO KOHEI , MATSUYAMA KEISUKE
IPC分类号： F16J15/22 , F01D11/00 , F01D25/00 , F02C7/28 , F16J15/3292 , F16J15/447
CPC分类号： F01D11/12 , F01D11/001 , F05D2220/32 , F05D2240/56 , F05D2240/59 , F05D2250/13 , F05D2250/131 , F05D2250/182 , F05D2250/184 , F05D2250/232 , F05D2260/30 , F16J15/22 , F16J15/3288 , F16J15/3292 , F16J15/447 , F16J15/4472
摘要： A seal device for a turbine is disposed around a rotor so as to separate a high-pressure space and a low-pressure space and includes: a plurality of thin plates arranged along an outer peripheral surface of the rotor, each of the thin plates having a thin-plate tip surface facing the outer peripheral surface of the rotor; a first side plate disposed so as to face the high-pressure space and covering outer peripheral regions of first side surfaces, on a side of the high-pressure space, of the plurality of thin plates; and a second side plate disposed so as to face the low-pressure space and covering outer peripheral regions of second side surfaces, on a side of the low-pressure space, of the plurality of thin plates. The first side surface of each of the thin plates is covered with the first side plate in a region extending further to an inner side, in a radial direction of the rotor, than a region of the second side surface covered with the second side plate. A radial-directional position of the thin-plate tip surface of each of the thin plates has such a distribution that the side of the high-pressure space is farther away from the outer peripheral surface of the rotor than the side of the low-pressure space in at least a partial range of the thin-plate tip surface in an axial direction of the rotor, and the radial-directional position of the thin-plate tip surface at an axial-directional position closest to the high-pressure space is positioned on an inner side of an inner peripheral edge of the first side plate in the radial direction.

4. 发明公开

EP3260661A1 AIRFOIL WITH VARIABLE SLOT DECOUPLING 有权转让
标题翻译：带有可变插槽去耦的AIRFOIL
公开(公告)号：EP3260661A1
公开(公告)日：2017-12-27
申请号：EP17167805.5
申请日：2017-04-24
申请人： General Electric Company
发明人： WALUNJ, Jalindar Appa , HONKOMP, Mark Steven
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/147 , F02C7/12 , F05D2220/32 , F05D2240/304 , F05D2240/35 , F05D2250/184 , F05D2260/202 , F05D2260/2212
摘要： The present invention is directed to an airfoil (120) for a gas turbine rotor blade (100), including a plurality of internal cavities (138) within the airfoil (120). A plurality of pins (150) is disposed within an internal cavity (138) at the trailing edge (136). The trailing edge portion (136) defines a plurality of cooling passages (164(a)-(c)), each having an inlet (166(a)-(c)) and an outlet (168(a)-(c)). The cooling passages (164(a)-(c)) may have different lengths (176(a)-(b)) and diameters (170(a)-(c)) for increasing heat transfer. The plurality of pins (150) comprises a first subsetof pins (152) extending from the inner surface of the pressure side (130) to the inner side of the suction surface (132). The second subset of pins (154) extend merely to a position within the internal cavity (138). Thus, cooling efficiency of the airfoil is improved.
摘要翻译：本发明涉及一种用于燃气轮机转子叶片（100）的翼型件（120），其包括翼型件（120）内的多个内腔（138）。多个销（150）设置在后缘（136）处的内腔（138）内。后缘部分136限定多个具有入口166（a） - （c）和出口168（a） - （c）的冷却通道164（a） - （c））。为了增加传热，冷却通道（164（a） - （c））可以具有不同的长度（176（a） - （b））和直径（170（a） - （c））。多个销（150）包括从压力侧（130）的内表面延伸到吸力表面（132）的内侧的销（152）的第一子集。销（154）的第二子集仅延伸到内腔（138）内的位置。因此，翼型的冷却效率得到改善。

5. 发明公开

EP3255247A1 TURBINE COMPONENT AND METHODS OF MAKING AND COOLING A TURBINE COMPONENT 有权转让
标题翻译：涡轮机部件和制造和冷却涡轮机部件的方法
公开(公告)号：EP3255247A1
公开(公告)日：2017-12-13
申请号：EP17174357.8
申请日：2017-06-02
申请人： General Electric Company
发明人： DUTTA, Sandip , ZHANG, James , ITZEL, Gary Michael , DELVAUX, John McConnell , HAFNER, Matthew Troy
IPC分类号： F01D5/14 , F01D5/18 , F01D5/28
CPC分类号： F01D5/187 , B22F3/1055 , B22F3/24 , B22F2998/10 , B23K15/0086 , B23K15/0093 , B23K26/0006 , B23K26/342 , B23K26/70 , B23K2201/001 , B23K2203/08 , B33Y10/00 , B33Y80/00 , C23C28/042 , F01D5/147 , F01D5/282 , F01D9/02 , F01D25/12 , F05D2220/30 , F05D2230/22 , F05D2230/30 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2260/20 , F05D2260/204 , F05D2300/175 , F05D2300/6033
摘要： A turbine component (10) includes a root (11) and an airfoil (12) extending from the root (11) to a tip (14) opposite the root (11). The airfoil (12) forms a leading edge (15) and a trailing edge portion (42) extending to a trailing edge (16). A plurality of nested cooling channels (40) in the trailing edge portion (42) of the airfoil (12) permit passage of a cooling fluid from an interior of the turbine component (10) to an exterior of the turbine component (10) at the trailing edge portion (42). A method of making a turbine component (10) includes forming an airfoil (12) having a leading edge (15), a trailing edge portion (42) extending to a trailing edge (16), and a plurality of nested cooling channels (40) in the trailing edge portion (42). Each nested cooling channel fluidly connects an interior of the turbine component (10) with an exterior of the turbine component (10) at the trailing edge portion (42). A method of cooling a turbine component (10) is also disclosed.
摘要翻译：涡轮机部件（10）包括根部（11）和从根部（11）延伸到与根部（11）相对的尖端（14）的翼型件（12）。翼型件（12）形成延伸到后缘（16）的前缘（15）和后缘部分（42）。翼型件（12）的后缘部分（42）中的多个嵌套冷却通道（40）允许冷却流体从涡轮部件（10）的内部通到涡轮部件（10）的外部后缘部分（42）。一种制造涡轮机部件（10）的方法包括形成具有前缘（15）的翼型件（12），延伸到后缘（16）的后缘部分（42）以及多个嵌套的冷却通道（40 ）在后缘部分（42）中。每个嵌套的冷却通道在后缘部分（42）处将涡轮部件（10）的内部与涡轮部件（10）的外部流体连接。还公开了一种冷却涡轮机构件（10）的方法。

6. 发明公开

EP3255245A1 TURBINE COMPONENT AND METHODS OF MAKING AND COOLING A TURBINE COMPONENT 有权转让
标题翻译：涡轮机部件和制造和冷却涡轮机部件的方法
公开(公告)号：EP3255245A1
公开(公告)日：2017-12-13
申请号：EP17174318.0
申请日：2017-06-02
申请人： General Electric Company
发明人： DUTTA, Sandip , ZHANG, James , ITZEL, Gary Michael , DELVAUX, John McConnell , HAFNER, Matthew Troy
IPC分类号： F01D5/14 , F01D5/18 , F01D5/28
CPC分类号： F01D5/186 , F01D5/147 , F01D5/187 , F01D5/282 , F01D9/041 , F01D25/005 , F01D25/12 , F05D2230/22 , F05D2230/237 , F05D2230/31 , F05D2240/122 , F05D2240/304 , F05D2250/183 , F05D2250/184 , F05D2250/185 , F05D2260/202 , F05D2260/204 , F05D2300/175 , F05D2300/6033
摘要： A turbine component (10) includes a root (11) and an airfoil (12) extending from the root (11) to a tip (14) opposite the root (11). The airfoil (12) forms a leading edge (15) and a trailing edge portion (42) extending to a trailing edge (16). A plurality of axial cooling channels (40) in the trailing edge portion (42) of the airfoil (12) are arranged to permit axial flow of a cooling fluid from an interior of the turbine component (10) at the trailing edge portion (42) to an exterior of the turbine component (10) at the trailing edge portion (42). A method of making a turbine component (10) includes forming an airfoil (12) having a trailing edge portion (42) with axial cooling channels (40). The axial cooling channels (40) are arranged to permit axial flow of a cooling fluid from an interior to an exterior of the turbine component (10) at the trailing edge portion (42). A method of cooling a turbine component (10) is also disclosed.
摘要翻译：涡轮机部件（10）包括根部（11）和从根部（11）延伸到与根部（11）相对的尖端（14）的翼型件（12）。翼型件（12）形成延伸到后缘（16）的前缘（15）和后缘部分（42）。翼型件（12）的后缘部分（42）中的多个轴向冷却通道（40）布置成允许冷却流体从后缘部分（42）处的涡轮机部件（10）的内部轴向流动）到达后缘部分（42）处的涡轮机部件（10）的外部。一种制造涡轮机部件（10）的方法包括形成具有带有轴向冷却通道（40）的后缘部分（42）的翼型件（12）。轴向冷却通道（40）布置成允许冷却流体在后缘部分（42）处从涡轮部件（10）的内部轴向流动到外部。还公开了一种冷却涡轮机构件（10）的方法。

7. 发明授权

EP2511476B1 TURBINE 有权转让
公开(公告)号：EP2511476B1
公开(公告)日：2017-11-22
申请号：EP09852033.1
申请日：2009-12-07
申请人： Mitsubishi Hitachi Power Systems, Ltd.
发明人： IIDA, Koichiro
IPC分类号： F01D5/22 , F01D5/20 , F01D11/08 , F01D5/14
CPC分类号： F01D11/08 , F01D5/143 , F01D5/225 , F05D2250/184 , F05D2250/314 , F05D2250/38 , F05D2250/71
摘要： Disclosed are a turbine and turbine rotor blade that can improve performance while ensuring turbine rotor blade strength. Said turbine is provided with: a rotor blade (4) that rotates around a rotation axis (C) inside a main flow channel (2) in a casing (3); a stator vane (5) disposed inside the casing (3); a tip shroud (42) disposed on the radially outside tip of the rotor blade (4), the length of said tip shroud along the rotation axis (C) decreasing with increasing separation from the rotor blade (4); and a cavity section (32) formed inside the casing (3) at a position opposite the rotor blade (4). The tip shroud (42) fits inside the cavity section. The angle of inclination (0b) of the inner surface of the tip shroud (42) is larger than the angle of inclination of the inner surface of the casing (3), which is also the average angle of inclination (¸a) from the trailing edge of the stator vane (5), which is disposed upstream with respect to the main flow, to the cavity section (32), which is disposed downstream with respect to the main flow.

8. 发明公开

EP2557270A3 Airfoil including trench with contoured surface 有权转让
标题翻译：包括带有轮廓表面的沟槽的翼型
公开(公告)号：EP2557270A3
公开(公告)日：2017-11-08
申请号：EP12179677.5
申请日：2012-08-08
申请人： United Technologies Corporation
发明人： Piggush, Justin D. , Kohli, Atul
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/145 , F01D9/065 , F05D2240/303 , F05D2240/305 , F05D2250/184 , F05D2250/294 , F05D2260/202
摘要： A airfoil (40) comprises a wall, a cooling channel (56), a trench (48) and a plurality of leading edge cooling holes (46). The wall has a leading edge (42), a trailing edge (44), a pressure side (50), a suction side (52), an outer diameter end and an inner diameter end to define an interior. The cooling channel (56) extends radially through the interior of the wall between the pressure side (50) and the suction side (52) and along the leading edge (44). The trench (48) extends radially along an exterior of the wall at the leading edge (44) and is recessed axially into the leading edge (44) to form a back wall (64). The back wall is contoured to include at least one undulation. The plurality of leading edge cooling holes (46) extends through the back wall (64) of the trench (48) to connect the interior of the wall at the cooling channel (56) to the exterior.
摘要翻译：翼型件（40）包括壁，冷却通道（56），沟槽（48）和多个前缘冷却孔（46）。该壁具有限定内部的前缘（42），后缘（44），压力侧（50），吸力侧（52），外径端和内径端。冷却通道56在压力侧50和吸入侧52之间沿着前缘44径向延伸穿过壁的内部。沟槽（48）在前缘（44）处沿着壁的外部径向延伸并且轴向地凹入前缘（44）中以形成后壁（64）。后壁的轮廓包括至少一个起伏。多个前缘冷却孔（46）延伸穿过沟槽（48）的后壁（64）以将冷却通道（56）处的壁的内部连接至外部。

9. 发明公开

EP3212893A2 FILM COOLED ENGINE COMPONENT FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于燃气涡轮发动机的薄膜冷却发动机部件
公开(公告)号：EP3212893A2
公开(公告)日：2017-09-06
申请号：EP15848165.5
申请日：2015-10-28
申请人： General Electric Company
发明人： BUNKER, Ronald, Scott , STONE, Timothy, Deryck
IPC分类号： F01D5/18 , F23R3/00
CPC分类号： F01D5/186 , F05D2250/181 , F05D2250/184 , F05D2250/24 , F05D2250/292 , F05D2250/294 , F05D2250/51 , F05D2250/70 , F05D2260/202 , F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/03042 , Y02T50/672 , Y02T50/676
摘要： An engine component for a gas turbine engine includes a film-cooled wall having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The wall includes one or more film holes that have an outlet provided on the hot surface and a contoured inlet provided on the cooling surface. A contoured portion in the cooling surface encompasses the inlets for two or more film holes in the wall.
摘要翻译：用于燃气涡轮发动机的发动机部件包括薄膜冷却壁，其具有面向热燃烧气体的热表面和面向冷却流体流动的冷却表面。壁包括一个或多个膜孔，其具有设置在热表面上的出口和设置在冷却表面上的成形入口。冷却表面中的轮廓部分包围壁上两个或更多个薄膜孔的入口。

10. 发明公开

EP1953341A3 Turbomachine blade and method of design 审中-公开
标题翻译：涡轮机叶片和设计方法
公开(公告)号：EP1953341A3
公开(公告)日：2017-07-05
申请号：EP08250021.6
申请日：2008-01-03
申请人： Rolls-Royce plc
发明人： Wilson, Alexander George , Stieger, Roy Douglas , Smith, Nigel , Coupland, John
IPC分类号： F01D5/14 , F01D5/16 , F02K3/06 , F04D21/00 , F04D29/32
CPC分类号： F01D5/141 , F02K3/06 , F04D21/00 , F04D29/324 , F05D2240/121 , F05D2240/303 , F05D2250/184 , F05D2260/96 , Y02T50/673
摘要： A blade for a turbomachine extends in use, in a radial direction relative to the axis of the turbomachine. The turbomachine has at least one operating condition which generates supersonic fluid flow at the blade. The blade is adapted to provide, at the supersonic operating condition, a leading edge sweep angle which varies such that successive radial positions (i) to (iii) along the leading edge are at respective sweep angle turning points. Position (i) is the radially inner and position (iii) the radially outer of the positions. Position (i) is at or radially outward of the 30% span position, where 0% span is the radially innermost point of the leading edge and 100% span is the radially outermost point of the leading edge. A corresponding turbo machine is also provided.
摘要翻译：用于涡轮机械的叶片在使用中相对于涡轮机械的轴线在径向方向上延伸。涡轮机具有至少一个在叶片处产生超音速流体流动的操作条件。叶片适于在超音速操作条件下提供前缘扫掠角，该前缘扫掠角变化使得沿前缘的连续径向位置（i）至（iii）位于相应的扫掠角转向点处。位置（i）是径向内部和位置（iii）位置的径向外部。位置（i）位于30％跨度位置或径向向外，其中0％跨度是前缘的径向最内点，100％跨度是前缘的径向最外点。还提供了相应的涡轮机。

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