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1. 发明授权

EP3205820B1 END WALL CONTOUR FOR AN AXIAL FLOW TURBINE STAGE 有权转让
公开(公告)号：EP3205820B1
公开(公告)日：2020-11-04
申请号：EP17152710.4
申请日：2017-01-23
申请人： General Electric Company
发明人： VENUGOPAL, Prem , STEIN, Alexander , OTTA, Shourya Prakash , SURESH, Ambady
IPC分类号： F01D5/14

2. 发明公开

EP3205820A1 END WALL CONTOUR FOR AN AXIAL FLOW TURBINE STAGE 有权转让
标题翻译：用于轴流式涡轮级的端壁轮廓
公开(公告)号：EP3205820A1
公开(公告)日：2017-08-16
申请号：EP17152710.4
申请日：2017-01-23
申请人： General Electric Company
发明人： VENUGOPAL, Prem , STEIN, Alexander , OTTA, Shourya Prakash , SURESH, Ambady
IPC分类号： F01D5/14
摘要： A turbine stage includes a row of airfoils 14 joined to corresponding platforms to define flow passages therebetween. Each airfoil includes opposite pressure 20 and suction 22 sides and extends in chord between opposite leading 24 and trailing 28 edges. Each platform has a contoured flow surface including a purge valley 38, an elevated bulge 46 and a bowl 48. The purge valley has a maximum depth at an elevation equal to or greater than a nominal axisymmetric platform surface of the corresponding platform. The purge valley extending tangentially against a purge cavity wall 41 and into the blend area and extending axially from proximate the leading edge of a first airfoil toward the suction side of the first airfoil, and toward the leading edge of a second adjacent airfoil to channel a purge flow. The elevated bulge adjoins the pressure side aft of the leading edge and the bowl adjoins the suction side aft of the leading edge.
摘要翻译：涡轮机级包括连接到相应平台的一排翼型件14，以在其间限定流动通道。每个翼型包括相反的压力20和吸力22侧，并且在相对的前缘24和后缘28之间的弦中延伸。每个平台具有包括净化谷38，升高的凸起46和碗48的波状流动表面。净化谷在等于或大于相应平台的标称轴对称平台表面的高度处具有最大深度。清洗谷相对于清洗腔壁41切向延伸并进入混合区域并从第一翼型的前缘附近朝向第一翼型的吸力侧轴向延伸并且朝向第二相邻翼型的前缘延伸以引导清除流量。升高的凸起与前缘的压力侧邻接，并且碗与前缘的吸力侧相邻。

3. 发明公开

EP3165712A1 GAS TURBINE ENGINE HAVING A FLOW CONTROL SURFACE WITH A COOLING CONDUIT 审中-公开
标题翻译：带有冷却导管的流量控制表面的燃气涡轮发动机
公开(公告)号：EP3165712A1
公开(公告)日：2017-05-10
申请号：EP16197022.3
申请日：2016-11-03
申请人： General Electric Company
发明人： DEDE, Mehmet Muhittin , ATSUCHI, Satoshi , PRITCHARD, Byron Andrew , KRAMMER, Erich Alois , JOTHIPRASAD, Giridhar , OTTA, Shourya Prakash , BOURASSA, Corey
IPC分类号： F01D5/08 , F01D9/04 , F01D9/06 , B01D45/16 , F04D29/54 , F02C7/18
CPC分类号： F02C7/18 , B01D45/16 , F01D5/081 , F01D9/041 , F01D9/065 , F02C7/052 , F04D29/542 , F04D29/584 , F05D2240/124 , F05D2250/51 , F05D2260/232 , F05D2260/607 , Y02T50/671 , Y02T50/676
摘要： The invention relates to a gas turbine engine 10 comprising a casing 46 having a compressor section 22, combustion section 28 and turbine section 32, axially arranged in a flow direction about a rotational axis 12 of the engine 10. The engine 10 includes a rotor 51 located within the casing 46 and rotatable about the rotational axis 12, including multiple sets of circumferentially arranged blades 56, 58, with at least one set corresponding to the compressor section 22 and another set corresponding to the turbine section 32. The engine 10 also includes a set of vanes 60, 62, 63 circumferentially arranged about the rotational axis 12 and at a location upstream of the combustion section 28, with the vanes 60, 62, 63 having a pressure side and a suction side. The engine 10 further includes a cooling conduit 120 extending from upstream of the combustion section 28 to downstream of the combustion section 28, with an inlet 118 located on the suction side of at least one of the vanes 60, 62, 63 which allows cooling air 94 to enter the inlet 118 and is directed through the cooling conduit 120 for cooling.
摘要翻译：燃气涡轮发动机10本发明涉及一种燃气涡轮发动机10，其包括具有压缩机部分22，燃烧部分28和涡轮部分32的壳体46，其围绕发动机10的旋转轴线12沿流动方向轴向布置。发动机10包括转子51 其位于壳体46内并且可围绕旋转轴线12旋转，包括多组沿圆周布置的叶片56,58，其中至少一组对应于压缩机部段22，另一组对应于涡轮机部段32.发动机10还包括一组叶片60,62,63围绕旋转轴线12周向布置并且位于燃烧部分28的上游位置，其中叶片60,62,63具有压力侧和吸力侧。发动机10还包括从燃烧部分28的上游延伸到燃烧部分28的下游的冷却导管120，其中入口118位于至少一个叶片60,62,63的吸入侧，其允许冷却空气 94进入入口118并被引导通过冷却导管120以进行冷却。

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