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1. 发明授权

EP2728124B1 Turbinenring und Strömungsmaschine 有权
公开(公告)号：EP2728124B1
公开(公告)日：2018-12-12
申请号：EP12190481.7
申请日：2012-10-30
申请人： MTU Aero Engines AG
发明人： Feldmann, Manfred
IPC分类号： F01D11/08 , F01D11/18
CPC分类号： F01D11/18 , F01D11/08 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F16J15/445

2. 发明公开

EP3351735A1 TURBOMASCHINENGEHÄUSEELEMENT 审中-实审
公开(公告)号：EP3351735A1
公开(公告)日：2018-07-25
申请号：EP17152728.6
申请日：2017-01-23
申请人： MTU Aero Engines AG
发明人： Albers, Lothar
IPC分类号： F01D9/04 , F01D11/08 , F01D11/24 , F01D25/12 , F01D25/14 , F01D25/24 , F01D25/26
CPC分类号： F01D25/145 , B33Y80/00 , F01D9/04 , F01D11/08 , F01D11/122 , F01D11/127 , F01D11/18 , F01D11/24 , F01D25/12 , F01D25/14 , F01D25/24 , F01D25/246 , F01D25/26 , F04D29/164 , F04D29/526 , F04D29/5853 , F05D2220/32 , F05D2230/31 , F05D2260/231
摘要： Die vorliegende Erfindung betrifft ein Turbomaschinengehäuseelement (1), insbesondere für eine Verdichter- oder Turbinenstufe einer Gasturbine, mit einem Strömungskanal (6) zur Aufnahme wenigstens eines Laufgitters (4) und einer ersten Kavität (2), die wenigstens teilweise mittels Urformens, insbesondere eines generativen Herstellungsverfahrens, hergestellt ist, wobei die ersten Kavität (2) zur passiven Wärmedämmung und/oder das montagefähige Turbomaschinengehäuseelement (1) nicht zur aktiven Umwälzung von Fluid durch die ersten Kavität (2) eingerichtet ist und/oder zwischen der ersten Kavität (2) und dem Strömungskanal (6) eine separate Dichtung (3) an dem Turbomaschinengehäuseelement (1) befestigt ist und/oder die erste Kavität (2) sich in Axialrichtung des Strömungskanals (6) über wenigstens 20% einer minimalen axialen Länge des Turbomaschinengehäuseelements (1) auf Höhe der Kavität (2) und/oder einer minimalen axialen Länge der separaten Dichtung (3) erstreckt und/oder mit Luft oder einem wärmedämmenden Fluid gefüllt ist, dessen spezifische Wärmeleitfähigkeit λ wenigstens 10% kleiner als die spezifische Wärmeleitfähigkeit λ von Luft ist.

3. 发明授权

EP2570613B1 Blade Outer Air Seal Assembly Leading Edge Core Configuration 有权
标题翻译：叶片外部空气密封组件前缘核心配置
公开(公告)号：EP2570613B1
公开(公告)日：2018-05-02
申请号：EP12184439.3
申请日：2012-09-14
申请人： United Technologies Corporation
发明人： Thibodeau, Anne-Marie B.
IPC分类号： F01D11/00 , F01D9/04 , F01D25/24 , F01D11/08 , F01D11/18 , F01D11/24
CPC分类号： F01D11/005 , F01D9/04 , F01D9/041 , F01D11/001 , F01D11/08 , F01D11/18 , F01D11/24 , F01D25/246 , F05D2240/11 , F05D2250/13 , F05D2250/314 , F05D2250/75 , F05D2260/22141 , Y02T50/676
摘要： An example blade outer air seal assembly consists of a blade outer air seal (50) containing channels (66) that communicate cooling air through at least some of the blade outer air seal (50). The blade outer air seal (50) has at least one circumferentially extending barrier (78a, 78b) separating a leading channel (66a) into a forward portion and an aft portion. Cooling air outlets (68a) from the leading channel (66a) are exclusively coupled to the aft portion.

4. 发明公开

EP3236024A1 PRESSURE VESSEL AND TURBINE 审中-公开
标题翻译：压力容器和涡轮机
公开(公告)号：EP3236024A1
公开(公告)日：2017-10-25
申请号：EP15869602.1
申请日：2015-08-26
申请人： Mitsubishi Heavy Industries, Ltd.
发明人： HATANO, Kohei
IPC分类号： F01D25/24 , F02C7/00 , F16J12/00
CPC分类号： F01D25/265 , F01D3/025 , F01D11/18 , F01D25/24 , F02C7/00 , F05D2220/31 , F05D2260/30 , F16J12/00
摘要： In order to improve circularity in a casing (11) the cylindrical shape of which is divided into two parts in the radial direction, with the two divided ends (11Aa, 11Ba) being connected in the cylindrical shape by means of flanges (11C) protruding toward the outside in the radial direction, thickness-increasing parts (1), which are for increasing the thickness in the radial direction except at the two divided ends (11Aa, 11Ba) and the arc-shaped center sections (11Ab, 11Bb) farthest from the respective divided ends (11Aa, 11Ba), are formed between the two divided ends (11Aa, 11Ba) and the arc-shaped center sections (11Ab, 11Bb).
摘要翻译：为了改善其圆柱形在径向上被分成两部分的壳体（11）中的圆形度，两个分开的端部（11Aa，11Ba）通过突出的凸缘（11C）以圆柱形连接朝向径向外侧的厚度增加部分（1），所述厚度增加部分（1）用于增加除了分离的两个端部（11Aa，11Ba）和弧形中心部分（11Ab，11Bb）之外的径向厚度分别形成在两个分割端部（11Aa，11Ba）与圆弧状的中央部（11Ab，11Bb）之间，从各分割端部（11Aa，11Ba）开始。

5. 发明公开

EP3090139A4 BLADE TIP CLEARANCE SYSTEMS 有权转让
标题翻译： SCHAUFELSPITZENSPALTSYSTEME
公开(公告)号：EP3090139A4
公开(公告)日：2017-09-06
申请号：EP14883657
申请日：2014-11-19
申请人： UNITED TECHNOLOGIES CORP
发明人： DAVIS TIMOTHY M , PAULINO JOSE R , DUGUAY BRIAN
IPC分类号： F01D11/08 , F01D11/18
CPC分类号： F01D11/18 , F01D5/02 , F01D5/12 , F01D11/24 , F05D2220/32 , F05D2260/22141 , F05D2300/5021 , F05D2300/50212 , Y02T50/676

6. 发明公开

EP3209865A1 GAS TURBINE ENGINE WITH A TURBINE BLADE TIP CLEARANCE CONTROL SYSTEM 有权
标题翻译：燃气轮机发动机与涡轮叶片头间隙控制系统
公开(公告)号：EP3209865A1
公开(公告)日：2017-08-30
申请号：EP14795740.1
申请日：2014-10-23
申请人： Siemens Energy, Inc.
发明人： ZHANG, Jiping , PEPPERMAN, Barton M.
IPC分类号： F01D11/18
CPC分类号： F01D11/18 , F01D9/042 , F01D11/025 , F01D11/08 , F01D11/16 , F05D2240/11 , F05D2260/36 , F05D2260/38 , F05D2300/50212
摘要： A gas turbine engine (10) having a turbine blade tip clearance control system (12) for increasing the efficiency of the engine (10) by reducing the gap (14) between turbine blade tips (16) and radially outward ring segments (18) is disclosed. The turbine blade tip clearance control system (12) may include one or more clearance control bands (20) positioned radially outward of inner surfaces (22) of ring segments (18) and bearing against at least one outer surface (24) of the ring segments (18) to limit radial movement of the ring segments (18). During operation, the clearance control band (20) limits radial movement of the ring segments (18), and the turbine blade tips (16) do not have a pinch point during start-up transient conditions. In addition, the smallest gap (14) during turbine engine operation may be found at steady state operation of the gas turbine engine (10). Thus, the clearance control system (12) can set the gap (14) between turbine blade tips (16) and ring segments (18) to be zero at steady state operation.
摘要翻译：一种燃气涡轮发动机（10），具有通过减小涡轮叶片尖端（16）和径向外环段（18）之间的间隙（14）来增加发动机（10）的效率的涡轮叶片尖端间隙控制系统（12）被披露。涡轮机叶片顶端间隙控制系统（12）可以包括一个或多个间隙控制带（20），所述一个或多个间隙控制带（20）定位在环形段（18）的内表面（22）的径向外侧并抵靠环的至少一个外表面（24）（18），以限制环形部分（18）的径向运动。在操作期间，间隙控制带（20）限制环段（18）的径向运动，并且涡轮叶片尖端（16）在启动瞬态条件期间不具有夹点。另外，在涡轮发动机运行期间的最小间隙（14）可以在燃气涡轮发动机（10）的稳态运行中找到。因此，间隙控制系统（12）可以在稳态运行时将涡轮机叶片尖端（16）和环形部分（18）之间的间隙（14）设定为零。

7. 发明公开

EP3121388A3 CONTROL RINGS FOR USE IN A GAS TURBINE 有权转让
标题翻译：用于燃气轮机的控制环
公开(公告)号：EP3121388A3
公开(公告)日：2017-04-19
申请号：EP16157952.9
申请日：2016-02-29
申请人： United Technologies Corporation
发明人： BORJA, Mark
IPC分类号： F01D11/18
CPC分类号： F01D11/18 , F05D2240/11 , F05D2300/5023 , F05D2300/5024
摘要： The present disclosure concerns three different types of control rings with adapted thermal response for gas turbines. A first control ring (101) for use in a gas turbine engine (20) includes a control ring segment (107) defining a centerline axis. The control ring segment includes an inner diameter surface (111) and an outer diameter surface (113). A thermally isolating contact (115) is operatively connected to at least one of the inner diameter surface and the outer diameter surface. The thermally isolating contact has lower thermal conductivity than the control ring. Furthermore, another control ring for use in a gas turbine engine comprises a control ring segment defining a centerline axis, wherein the control ring segment includes an inner diameter surface and an outer diameter surface, and an internal cavity defined between the inner and outer diameter surfaces, wherein the internal cavity is configured to contain a material having a higher heat capacitance than the control ring. An even further control ring for use in a gas turbine engine comprises a plurality of radially stacked rings, wherein each radially stacked ring includes a plurality of arcuate segments.
摘要翻译：本公开涉及三种不同类型的对燃气轮机具有适应的热响应的控制环。用于燃气涡轮发动机（20）的第一控制环（101）包括限定中心线轴线的控制环段（107）。控制环段包括内径表面（111）和外径表面（113）。隔热接触件（115）可操作地连接到内径表面和外径表面中的至少一个。隔热接触件的热导率低于控制环。此外，用于燃气涡轮发动机的另一控制环包括限定中心线轴线的控制环段，其中控制环段包括内径表面和外径表面以及限定在内径表面和外径表面之间的内腔其中，所述内腔构造成容纳具有比所述控制环更高的热容量的材料。用于燃气涡轮发动机的更进一步的控制环包括多个径向堆叠的环，其中每个径向堆叠的环包括多个弧形段。

8. 发明公开

EP3022398A4 TURBINE CLEARANCE CONTROL UTILIZING LOW ALPHA MATERIAL 审中-公开
标题翻译： TURBINENSPIELRAUMSTEUERUNG MIT NIEDRIGEM ALPHAMATERIALANTEIL
公开(公告)号：EP3022398A4
公开(公告)日：2017-03-01
申请号：EP14825893
申请日：2014-07-02
申请人： UNITED TECHNOLOGIES CORP
发明人： SUCIU GABRIEL L , ALVANOS IOANNIS
IPC分类号： F01D11/18 , F01D5/28 , F01D5/34 , F01D11/12
CPC分类号： F01D5/28 , F01D5/34 , F01D11/122 , F01D11/18 , F02C3/04 , F05D2300/174 , Y02T50/671

9. 发明公开

EP3090139A2 BLADE TIP CLEARANCE SYSTEMS 有权转让
标题翻译： SCOOP TOP分体式系统
公开(公告)号：EP3090139A2
公开(公告)日：2016-11-09
申请号：EP14883657.0
申请日：2014-11-19
申请人： United Technologies Corporation
发明人： DAVIS, Timothy M. , PAULINO, Jose R. , DUGUAY, Brian
IPC分类号： F01D11/08 , F01D11/18
CPC分类号： F01D11/18 , F01D5/02 , F01D5/12 , F01D11/24 , F05D2220/32 , F05D2260/22141 , F05D2300/5021 , F05D2300/50212 , Y02T50/676
摘要： A blade tip clearance system includes first and second control rings. The first control ring has a first coefficient of thermal expansion (CTE) and a first thermal response rate. The second control ring is located radially outward of and operatively connected to the first control ring and has a second CTE that is different from the first CTE and a second thermal response rate that is different from the first thermal response rate. Thermal expansion and contraction of the first and the second control rings controls a radial position of the blade tip clearance system relative to a rotating blade component.

10. 发明公开

EP3042044A1 A GAS TURBINE LAMINATE SEAL ASSEMBLY COMPRISING FIRST AND SECOND HONEYCOMB LAYER AND A PERFORATED INTERMEDIATE SEAL PLATE IN-BETWEEN 审中-公开
标题翻译： FOR第一和第二WABEN波状层燃气轮机层压密封装置和穿孔间密封板之间
公开(公告)号：EP3042044A1
公开(公告)日：2016-07-13
申请号：EP14755514.8
申请日：2014-08-13
申请人： General Electric Company
发明人： GONYOU, Craig Alan , UPDIKE, Gregory Allen
IPC分类号： F01D11/02 , F01D11/12
CPC分类号： F01D11/18 , F01D11/025 , F01D11/12 , F05D2220/32 , F05D2230/237 , F05D2230/50 , F05D2240/10 , F05D2240/20 , F05D2250/283 , Y02T50/672
摘要： A laminate seal assembly (34), disposed on a stator seal portion (33) and opposite a rotor seal portion (35) of a gas turbine engine (10) comprises a first honeycomb layer (40) having a first edge (42) which engages the rotor portion and a second edge (44) distal from said rotor seal portion, a plurality of honeycomb cells (41) extending between the first edge and the second edge, an intermediate seal plate (50) having a first material surface (51) and a second material surface (53), the first material surface disposed against the second edge of the first honeycomb layer, a low conductivity structure (60) disposed on the second surface, and a backing plate (70) disposed on against said low conductivity structure, wherein the stator portion may be tuned for thermal growth to match the thermal growth of the rotor portion.

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