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1. 发明公开

EP4423376A1 DETECTION D'UN VENT DE TRAVERS SUR UNE TURBOMACHINE A PARTIR DES DONNEES DU MOTEUR 审中-实审
公开(公告)号：EP4423376A1
公开(公告)日：2024-09-04
申请号：EP22801865.1
申请日：2022-10-19
申请人： SAFRAN AIRCRAFT ENGINES
发明人： GARNIER, Alméric
IPC分类号： F02C7/04 , F02K3/06 , G01P13/02 , G01P5/14 , G05D1/08
CPC分类号： F02C7/04 , F02K3/06 , F05D2260/8020130101 , G01P5/14

3. 发明授权

EP3039341B1 CHAMBRE DE COMBUSTION DE TURBOMACHINE POURVUE DE MOYENS DE DÉFLECTION D'AIR POUR RÉDUIRE LE SILLAGE CREÉ PAR UNE BOUGIE D'ALLUMAGE 有权转让
公开(公告)号：EP3039341B1
公开(公告)日：2018-12-05
申请号：EP14790221.7
申请日：2014-10-02
申请人： Safran Aircraft Engines
发明人： LEGLAYE, François , BIDART, Olivier , PIREYRE, Pierre-François , PIEUSSERGUES, Christophe
IPC分类号： F23R3/04
CPC分类号： F02C7/04 , F02C3/04 , F02C7/18 , F02C7/264 , F02P15/003 , F23R3/04 , F23R3/06 , F23R3/16 , Y02T50/675

4. 发明授权

EP3019722B1 PLATED POLYMER COMPONENTS FOR A GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3019722B1
公开(公告)日：2018-11-21
申请号：EP14823557.5
申请日：2014-07-09
申请人： United Technologies Corporation
发明人： DACUNHA, Nelson , BARNETT, Barry , LOMASNEY, Gary, M. , PARKOS, Joseph , ROACH, James, T , LEVASSEUR, Glenn , WATSON, Charles, R. , XU, Jinquan , COOK, III, Grant, O. , KERSEY, Raymond, K. , TWELVES, Wendell, V , BUGAJ, Shari, L.
IPC分类号： F02C7/00 , F02C7/30 , C25D5/56 , C25D1/00 , C25D7/00 , C23C18/16 , C23C18/31 , F01D5/28 , F01D5/30 , F01D9/04 , F01D25/00 , F01D25/30 , F01D25/24 , F02C7/04 , C25D5/02 , C25D5/10 , C25D7/04 , C25D7/06
CPC分类号： F01D5/3092 , C23C18/1641 , C23C18/1651 , C23C18/1657 , C23C18/31 , C25D1/00 , C25D5/022 , C25D5/10 , C25D7/00 , C25D7/04 , C25D7/0607 , F02C7/04 , F02K1/54 , F05D2230/90 , F05D2260/96 , F05D2300/43 , 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.

5. 发明授权

EP3081781B1 NOSE CONE ASSEMBLY AND METHOD OF CIRCULATING AIR IN A GAS TURBINE ENGINE 有权转让
公开(公告)号：EP3081781B1
公开(公告)日：2018-09-12
申请号：EP16165146.8
申请日：2016-04-13
申请人： United Technologies Corporation
发明人： SUCIU, Gabriel L. , CHANDLER, Jesse M. , HIPSKY, Harold W. , ZYWIAK, Thomas M.
IPC分类号： F02C7/04 , B64C11/14 , F02C7/18 , F02C7/14 , F01D25/12
CPC分类号： F02C7/04 , B64C11/14 , F01D25/12 , F02C7/14 , F02C7/18 , F05D2220/32 , F05D2260/213
摘要： A nose cone assembly (64) for a gas turbine engine (20) and method (200) of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone (66) having an aperture (68) communicating air to an interior space (76) of the nose cone and a discharge member (74) communicating the air out of the nose cone.

6. 发明公开

EP3360665A1 BONDING OF TURBOMACHINERY COMPONENTS 无效
公开(公告)号：EP3360665A1
公开(公告)日：2018-08-15
申请号：EP18152754.0
申请日：2018-01-22
申请人： Rolls-Royce plc
发明人： Backhouse, Robert C
IPC分类号： B29C65/34 , B29C65/48 , B29C65/76 , F01D25/24 , B32B37/06 , B32B37/12 , B32B43/00 , G01N25/18 , B29C65/82 , B29L31/30
CPC分类号： B32B37/06 , B29C65/344 , B29C65/3492 , B29C65/4815 , B29C65/4835 , B29C65/76 , B29C65/8253 , B29C66/1122 , B29C66/532 , B29C66/721 , B29C66/7212 , B29C66/9141 , B29C66/91651 , B29C66/919 , B29L2031/3076 , B32B5/028 , B32B7/12 , B32B37/1207 , B32B43/006 , B32B2037/1253 , B32B2262/106 , B32B2307/202 , F02C7/04 , F02C7/047 , F02K1/827 , F04D29/023 , F05D2220/32 , F05D2230/40 , F05D2260/30 , G01N25/18 , Y02T50/672 , B29K2307/04
摘要： This disclosure concerns a composite product having first (12) and second (14) components. At least one intermediate binding layer (16) is located between the first (12) and second (14) components, and at least one electrically conductive member (24) is located within the at least one intermediate layer (16). The at least one electrically conductive member (24) is configured to generate thermal energy upon the application of an electrical current to the at least one electrically conductive member (24). The at least one intermediate layer (16) is configured such that at least one characteristic of the at least one intermediate layer (16) is altered where the thermal energy generated by the at least one electrically conductive member (24) is above a pre-determined threshold.

7. 发明授权

EP2864619B1 TURBOMACHINE FLOW STABILITY ENHANCEMENT DEVICE CONTROL 有权
公开(公告)号：EP2864619B1
公开(公告)日：2018-08-15
申请号：EP13807726.8
申请日：2013-06-04
申请人： United Technologies Corporation
发明人： MORFORD, Stephen A.
IPC分类号： F02K3/00 , F02C9/00 , F02C7/00 , F02C7/04
CPC分类号： B64D33/02 , B64D2033/0226 , F02C7/04 , F05D2270/17
摘要： An example method of controlling a flow enhancement device includes providing a flow enhancement device that is configured stabilize a flow of air near a nacelle. The flow enhancement device has a first setting and a second setting that provides more stabilization than the first setting. The method includes monitoring parameters of a turbomachine to determine the stability of the flow of air near the nacelle. The method also adjusts the flow enhancement device between the first setting and the second setting based on the monitoring.

8. 发明公开

EP2369155A3 A gas turbine engine nose cone 有权转让
标题翻译：燃气涡轮发动机鼻锥
公开(公告)号：EP2369155A3
公开(公告)日：2018-04-04
申请号：EP11157612.0
申请日：2011-03-10
申请人： Rolls-Royce plc
发明人： Bottome, Kristofer
IPC分类号： F02C7/04 , B64C11/14
CPC分类号： H01M6/08 , B64C11/14 , F02C7/04 , F05D2250/232 , F05D2300/603 , H01M2/0235 , H01M2/30
摘要： A gas turbine engine nose cone assembly (40) comprises a tapering spinner (42). The tapering spinner (42) has a point (44) at a first end (46) and a circular base (48) at a second end (50). The tapering spinner (42) comprises a carbon fibre containing composite material layer (70), an electrically insulating layer (74) arranged on an inner surface (72) of the carbon fibre containing composite material layer (70), an electrically conducting layer (78) arranged on an inner surface (76) of the electrically insulating layer (74) and an electrically conducting member (80) extends through the first end of the tapering spinner (42) and is connected to the electrically conducting layer (78). This arrangement provides lightning protection for the gas turbine engine nose cone assembly (40).
摘要翻译：燃气涡轮发动机鼻锥组件（40）包括锥形旋转器（42）。锥形旋转器（42）在第一端（46）处具有点（44），在第二端（50）处具有圆形基部（48）。锥形旋转器（42）包括含碳纤维复合材料层（70），设置在含碳纤维复合材料层（70）的内表面（72）上的电绝缘层（74），导电层布置在电绝缘层（74）的内表面（76）上的导电构件（78）和导电构件（80）延伸穿过锥形旋转器（42）的第一端并连接到导电层（78）。该布置为燃气涡轮发动机鼻锥组件（40）提供防雷保护。

9. 发明公开

EP3242003A3 LIQUID INJECTION APPARATUS AND COMPRESSOR ASSEMBLY HAVING THE SAME 有权转让
标题翻译：液体注射装置和具有该装置的压缩机组件
公开(公告)号：EP3242003A3
公开(公告)日：2018-03-14
申请号：EP17168343.6
申请日：2017-04-27
申请人： General Electric Company
发明人： MERCHANT, Laxmikant , PONYAVIN, Valery Ivanovich , MILLS, Jeffrey Patrick , KOTHAKAPU, Divya Reddy , YU, Weilun , BAGWELL, Joshua Adam
IPC分类号： F02C3/30 , F02C7/04 , F02C7/143
CPC分类号： F04C29/12 , F02C3/30 , F02C7/04 , F02C7/1435 , F04C29/02 , F04C29/04 , F05D2230/51
摘要： A liquid injection apparatus for use with a compressor 108 having a rotor shaft 128 and a casing part 122 is provided. The liquid injection apparatus 146 includes at least one conduit and at least one nozzle coupled to the conduit(s). The liquid injection apparatus is panel-shaped and has a first panel segment, a second panel segment, and at least one of: a passage defined between the first panel segment and the second panel segment, the passage sized to receive at least one of the rotor shaft and the casing part; and a third panel segment positioned between the first panel segment and the second panel segment. The third panel segment is at least in part detachable from the first panel segment and/or the second panel segment for receiving at least one of the rotor shaft and the casing part between the first panel segment and the second panel segment.
摘要翻译：提供了一种用于具有转子轴128和壳体部分122的压缩机108的液体喷射设备。液体注射装置146包括至少一个导管和至少一个与导管连接的喷嘴。该液体注射设备是面板形状的并且具有第一面板节段，第二面板节段和以下中的至少一个：限定在第一面板节段和第二面板节段之间的通道，该通道的尺寸被设计成接收至少一个转子轴和壳体部分; 以及位于第一面板部分和第二面板部分之间的第三面板部分。第三面板部分至少部分地可从第一面板部分和/或第二面板部分拆卸，以用于在第一面板部分和第二面板部分之间接收转子轴和壳体部分中的至少一个。

10. 发明公开

EP3289181A1 AUBE COMPOSITE, COMPRENANT UN RENFORT DE BORD D'ATTAQUE EN UN AUTRE MATERIAU 有权
标题翻译：复合材料AUB，包含另一种材料的侵蚀边缘加固
公开(公告)号：EP3289181A1
公开(公告)日：2018-03-07
申请号：EP16726129.6
申请日：2016-04-28
申请人： SAFRAN AIRCRAFT ENGINES
发明人： DAMIENS, Alexandre , POUZADOUX, Frédéric, Jean-Bernard , NOTARIANNI, Gilles, Pierre-Marie
IPC分类号： F01D5/14
CPC分类号： F04D29/388 , F01D5/147 , F01D5/282 , F01D5/288 , F02C7/04 , F05D2250/73 , F05D2300/133 , F05D2300/603 , Y02T50/672
摘要： The invention relates to a blade made of composite material, provided with a reinforcement (17) made of a stronger material with regard to a leading edge (5) likely to be struck by solid objects, which comprises, under the aerodynamic portion of the blade, extensions (18, 19) attached to the blade root. According to the invention, said extensions (18, 19) are dissymmetric, the extension (18) located on the suction side being generally further back from the leading edge (5) than the extension (19) on the pressure side.

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