-
公开(公告)号：US20170370374A1
公开(公告)日：2017-12-28
申请号：US15674865
申请日：2017-08-11
发明人： Hien DUONG , Krishna Prasad BALIKE , Thomas VEITCH , Keegan LOBO , Raman WARIKOO
摘要： A compressor rotor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented.
-
公开(公告)号：US20160061042A1
公开(公告)日：2016-03-03
申请号：US14469948
申请日：2014-08-27
发明人： Hien DUONG , Krishna Prasad BALIKE , Thomas VEITCH , Raman WARIKOO , Keegan LOBO
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/145 , F04D29/324 , F05D2240/303 , F05D2250/71
摘要： A rotary airfoil in a gas turbine engine is provided. The airfoil includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. An axial component of a center of gravity of a cross-section taken chordally toward the tip of the airfoil being upstream relative to an axial component of a center of gravity of a cross-section taken chordally toward the root of the airfoil. A method for forming such blade is also presented.
摘要翻译： 提供了一种在燃气涡轮发动机中的旋转翼型件。 翼型件包括相对的压力和吸力侧面，它们在弦向相对的前缘和后缘处连接在一起。 压力和吸力侧在从根部到尖端的跨度方向上延伸。 横截面的轴向分量是相对于翼型向翼面的根部截取的横截面的重心的轴向分量在翼面上朝向翼型的末端方向向上延伸的横截面的轴向分量。 还提出了一种用于形成这种刀片的方法。
-
公开(公告)号：US20180066522A1
公开(公告)日：2018-03-08
申请号：US15808060
申请日：2017-11-09
发明人： Raman WARIKOO , Krishna Prasad BALIKE , Keegan LOBO , Hien DUONG , Thomas VEITCH
CPC分类号： F01D5/141 , F01D9/041 , F04D29/324 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/301 , F05D2250/292
摘要： An airfoil for a gas turbine engine comprises at least three successive sections defined between a root and a tip. A first decrease of maximum thickness-to-chord ratios defined by a difference between a maximum thickness-to-chord ratio at the root and a maximum thickness-to-chord ratio at a first spanwise position, a second decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the first spanwise position and a maximum thickness-to-chord ratio at a second spanwise position, a third decrease of the maximum thickness-to-chord ratios defined by a difference between the maximum thickness-to-chord ratio at the second spanwise position and a maximum thickness-to-chord ratio at the tip, the second decrease being greater than the corresponding first and third decreases.
-
公开(公告)号：US20160146012A1
公开(公告)日：2016-05-26
申请号：US14553119
申请日：2014-11-25
发明人： Raman WARIKOO , Krishna Prasad BALIKE , Keegan LOBO , Hien DUONG , Thomas VEITCH
CPC分类号： F01D5/141 , F01D9/041 , F04D29/324 , F05D2220/32 , F05D2240/12 , F05D2240/30 , F05D2240/301 , F05D2250/292
摘要： An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil. The spanwise distribution of maximum thicknesses decreases from the root to the tip. In one aspect, the spanwise distribution is stepped between a first portion extending from the root and a second portion extending to the tip.
摘要翻译： 燃气涡轮发动机中的翼型件包括在弦向相对的前缘和后缘处连接在一起的相对的压力和吸力侧。 压力和吸力侧从翼面的根部延伸到尖端。 翼型件具有翼型的弦横截面的最大厚度的翼展方向分布。 最大厚度的翼展方向分布从根部向尖端减小。 在一个方面，翼展方向分布在从根部延伸的第一部分和延伸到尖端的第二部分之间是阶梯状的。
-
公开(公告)号：US20160061216A1
公开(公告)日：2016-03-03
申请号：US14469938
申请日：2014-08-27
发明人： Hien DUONG , Krishna Prasad BALIKE , Thomas VEITCH , Raman WARIKOO , Keegan LOBO
CPC分类号： F04D29/384 , F01D5/141 , F01D5/145 , F04D19/00 , F04D19/02 , F04D29/324 , F05D2240/303 , F05D2270/17
摘要： A compressor rotor airfoil in a gas turbine engine is presented. Opposed pressure and suction sides are joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend in a span direction from a root to a tip. A leading edge dihedral angle is defined at a point on the leading edge between a tangent to the airfoil and a vertical. The leading edge dihedral angle has a span-wise distribution. The distribution has at least one inflection point. A method of reducing a rub angle between a compressor rotor blade and a casing surrounding the blade is also presented.
摘要翻译： 提出了一种燃气涡轮发动机中的压缩机转子翼型件。 相反的压力和吸力侧在弦向相反的前缘和后缘连接在一起。 压力和吸力侧在从根部到尖端的跨度方向上延伸。 前缘二面角定义在翼型的切线与垂直线之间的前缘上的一点上。 前缘二面角具有跨度分布。 分布至少有一个拐点。 还提出了一种降低压缩机转子叶片和围绕叶片的壳体之间的摩擦角的方法。
-
-
-
-
搜索结果
5 条记录 (耗时 0.012 秒)
