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1. 发明公开

EP2806104A1 Aerofoil recambering 失效转让
标题翻译：曲率变化的翼形状
公开(公告)号：EP2806104A1
公开(公告)日：2014-11-26
申请号：EP14166295.7
申请日：2014-04-29
申请人： Rolls-Royce plc
发明人： Hield, Paul , Page, James , Tucker, Paul
IPC分类号： F01D5/14 , G06F17/50
CPC分类号： G06F17/50 , F01D5/141 , F01D9/02 , F05D2260/81 , G06F17/5018 , G06F2217/46 , Y02T50/673
摘要： A method of recambering an aerofoil section (48). A position on one of the surfaces that intersects with a passage shock (56) between adjacent aerofoils is determined and then projected as a shock position (60) onto the camber line (50). A shock region (62) encompassing the shock position (609 and extending in a chordal direction towards the leading and trailing edges (40,42) is defined. The camber line (50) is recalculated in an upstream region (65) using semi-inverse design. The camber line (50) is extrapolated across the shock region (62) to match a geometric criterion. The camber line (50) is recalculated in a downstream region using semi-inverse design.

2. 发明授权

EP2806104B1 Aerofoil recambering 失效转让
标题翻译： Wölbungsveränderungeines Schaufelprofils
公开(公告)号：EP2806104B1
公开(公告)日：2017-03-15
申请号：EP14166295.7
申请日：2014-04-29
申请人： Rolls-Royce plc
发明人： Hield, Paul , Page, James , Tucker, Paul
IPC分类号： F01D9/02 , F01D5/14 , G06F17/50
CPC分类号： G06F17/50 , F01D5/141 , F01D9/02 , F05D2260/81 , G06F17/5018 , G06F2217/46 , Y02T50/673
摘要： A method of recambering an aerofoil section (48). A position on one of the surfaces that intersects with a passage shock (56) between adjacent aerofoils is determined and then projected as a shock position (60) onto the camber line (50). A shock region (62) encompassing the shock position (609 and extending in a chordal direction towards the leading and trailing edges (40,42) is defined. The camber line (50) is recalculated in an upstream region (65) using semi-inverse design. The camber line (50) is extrapolated across the shock region (62) to match a geometric criterion. The camber line (50) is recalculated in a downstream region using semi-inverse design.
摘要翻译：检查机翼部分（48）的方法。确定与在相邻机翼之间的通道冲击（56）相交的一个表面上的位置，然后将其作为冲击位置（60）投影到弧形线（50）上。定义了围绕冲击位置（609并且朝向前缘和后缘（40,42））的弦方向延伸的冲击区域（62），在上游区域（65）中使用半圆形重新计算弧形线（50）反转设计，外弯线（50）在冲击区域（62）外推，以匹配几何准则，使用半反转设计在下游区域重新计算弧形线（50）。

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