公开(公告)号：WO2010057627A1

公开(公告)日：2010-05-27

申请号：PCT/EP2009/008216

申请日：2009-11-18

Applicant: ROLLS-ROYCE PLC ,  LUNG, Hang Wai ,  GOODHAND, Martin Neil ,  MILLER, Robert John ,  HOWARD, Michael Arthur

Inventor： LUNG, Hang Wai ,  GOODHAND, Martin Neil ,  MILLER, Robert John ,  HOWARD, Michael Arthur

IPC: F01D5/14 ,  F04D29/38 ,  F01D9/04 ,  F01D25/16 ,  F03D1/06 ,  B64C3/14 ,  B64C7/02 ,  B64C11/18 ,  B64D29/02 ,  B64D29/04

CPC classification number: F01D5/141 ,  B64C3/14 ,  B64C2003/146 ,  B64C2003/147 ,  F01D9/041 ,  F03D1/06 ,  F04D27/001 ,  F04D29/324 ,  F04D29/544 ,  F05B2240/301 ,  F05D2240/301 ,  F05D2250/70 ,  Y02E10/721 ,  Y02E10/726 ,  Y02T50/12 ,  Y02T50/673

Abstract: A method for defining the shape of an edge of an aerofoil comprises the following steps: obtaining a starting value for the thickness of the edge; defining a distance from the edge of the aerofoil in terms of the thickness; over the defined distance, defining a space S in terms of normalised camberline and normalised thickness; transforming the space S to a new space S'; parameterising the new space S' to obtain new values for normalised camberline and normalised thickness; defining a new shape for the edge using the new parameter values. In a preferred embodiment, the transforming step comprises applying a parabolic function to the space S.

Abstract translation: 用于限定机翼边缘形状的方法包括以下步骤：获得边缘厚度的起始值; 根据厚度限定与机翼边缘的距离; 在规定的距离上，以归一化的弯度和标准化的厚度来定义空间S; 将空间S转换为新空间S'; 参数化新空间S'以获得标准化曲线和归一化厚度的新值; 使用新的参数值为边缘定义新的形状。 在优选实施例中，变换步骤包括将抛物线函数应用于空间S.

公开(公告)号：WO2008001043A1

公开(公告)日：2008-01-03

申请号：PCT/GB2007/002226

申请日：2007-06-14

Applicant: ROLLS-ROYCE PLC ,  CARERON, Mitchel ,  LUNG, Hang, Wai ,  ORCHARD, Nicholas, Barrington ,  GOODER, Michael, John, Sheldon

Inventor： CARERON, Mitchel ,  LUNG, Hang, Wai ,  ORCHARD, Nicholas, Barrington ,  GOODER, Michael, John, Sheldon

IPC: G01B21/20 ,  F01D5/14 ,  G05B19/401

CPC classification number: G01B21/20 ,  F01D5/141 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/71 ,  F05D2250/74 ,  G05B19/401 ,  G05B2219/32228 ,  G05B2219/37064 ,  G05B2219/45147 ,  Y02T50/673

Abstract: The profile of an aerofoil blade is measured through centre line determination. Curves are fitted using a best-fit alogorithm separately to measured points on both sides of the blade. An intersection point of the curves defines the leading edge point, which is used in determining the centre line. The profile of the blade is determined with reference to the centre line.

Abstract translation: 翼面叶片的轮廓通过中心线测定来测量。 使用最佳拟合算法将曲线拟合到刀片两侧的测量点。 曲线的交点定义前缘点，用于确定中心线。 参考中心线确定叶片的轮廓。

公开(公告)号：WO2008001043A8

公开(公告)日：2009-01-29

申请号：PCT/GB2007002226

申请日：2007-06-14

Applicant: ROLLS ROYCE PLC ,  CAMERON MITCHEL ,  LUNG HANG WAI ,  ORCHARD NICHOLAS BARRINGTON ,  GOODER MICHAEL JOHN SHELDON

Inventor： CAMERON MITCHEL ,  LUNG HANG WAI ,  ORCHARD NICHOLAS BARRINGTON ,  GOODER MICHAEL JOHN SHELDON

IPC: G01B21/20 ,  F01D5/14 ,  G05B19/401

CPC classification number: G01B21/20 ,  F01D5/141 ,  F05D2230/80 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/71 ,  F05D2250/74 ,  G05B19/401 ,  G05B2219/32228 ,  G05B2219/37064 ,  G05B2219/45147 ,  Y02T50/673

Abstract: The profile of an aerofoil blade is measured through centre line determination. Curves are fitted using a best-fit alogorithm separately to measured points on both sides of the blade. An intersection point of the curves defines the leading edge point, which is used in determining the centre line. The profile of the blade is determined with reference to the centre line.

Abstract translation: 翼面叶片的轮廓通过中心线测定来测量。 使用最佳拟合算法将曲线拟合到刀片两侧的测量点。 曲线的交点定义前缘点，用于确定中心线。 参考中心线确定叶片的轮廓。