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公开(公告)号：US06481972B2
公开(公告)日：2002-11-19
申请号：US09741892
申请日：2000-12-22
IPC分类号： F03D1102
CPC分类号： F01D5/18 , F01D5/16 , F05D2230/21 , Y10S416/50 , Y10T29/4932 , Y10T29/49764
摘要： A tuning rib is added preferably in the aft cavity of a cored turbine bucket to alter the bucket's natural frequencies. The tuning rib may be a solid rib or a segmented rib and is particularly suited for altering high order frequency modes such as 2T, 4F and 1-3S. As such, detrimental crossings of natural bucket frequencies and gas turbine stimuli can be avoided to thereby improve the reliability of a gas turbine without impacting other features of the bucket that are important to the performance of the gas turbine.
摘要翻译： 调谐肋优选地添加在核心涡轮机桶的后腔中以改变铲斗的固有频率。 调音肋可以是实心肋或分段肋，并且特别适用于改变高阶频率模式，例如2T，4F和1-3S。 因此，可以避免天然桶频率和燃气轮机刺激的有害交叉，从而提高燃气轮机的可靠性，而不会影响对燃气轮机的性能很重要的桶的其他特征。
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公开(公告)号：US06461110B1
公开(公告)日：2002-10-08
申请号：US09901594
申请日：2001-07-11
申请人： Robert Romany By , Tommy Dee Hayes , Paul Francis Norton , Jon Conrad Schaeffer , Ariel Caesar-Prepena Jacala
发明人： Robert Romany By , Tommy Dee Hayes , Paul Francis Norton , Jon Conrad Schaeffer , Ariel Caesar-Prepena Jacala
IPC分类号： F01D514
CPC分类号： F01D5/141 , Y10S416/02
摘要： The first-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinates defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.
摘要翻译： 第一级铲斗具有基本上符合表I中列出的X，Y和Z的笛卡尔坐标值的翼型，其中Z是与垂直于涡轮机中心线的半径并且包含X和Y值的平面的垂直距离 其中Z值在翼型的径向最内部空气动力学部分的X，Y平面处开始为零，X和Y是在每个距离Z处限定翼型轮廓的坐标.X，Y和Z值可以被缩放为函数 相同的常数或数量，以提供用于铲斗的放大或缩小的翼型部分。
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公开(公告)号：US09359905B2
公开(公告)日：2016-06-07
申请号：US13405738
申请日：2012-02-27
申请人： Olivier Jacques Louis Lamicq , Fernando Manuel Ibarra Esparragoza , Paul Francis Norton , Jeremiah Wesley Key
发明人： Olivier Jacques Louis Lamicq , Fernando Manuel Ibarra Esparragoza , Paul Francis Norton , Jeremiah Wesley Key
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F05D2250/29 , F05D2250/712
摘要： A rotor blade for a gas turbine engine has an airfoil, a base integrally joined to the airfoil, and a root integrally joined to the base and mountable in a slot in a rotor hub of the gas turbine engine. The root has a dovetail including at least one contact face that, when mounted, contacts a surface of the slot to retain the rotor blade in the hub. The root includes a neck between the base and the dovetail, and a groove in the neck for redirecting stress in the rotor blade. In certain embodiments, the groove is at a distance from the at least one contact face, has a length less than a length of the dovetail, and/or has an initial non-zero depth at the side of a trailing edge of the airfoil and tapers to a zero depth in the direction of the leading edge of the airfoil.
摘要翻译： 用于燃气涡轮发动机的转子叶片具有翼型件，与翼型件一体地接合的基座，以及整体地连接到基座并可安装在燃气涡轮发动机的转子毂中的槽中的根部。 根部具有燕尾榫，包括至少一个接触面，当安装时，接触面接触槽的表面以将转子叶片保持在轮毂中。 根部包括在基部和燕尾榫之间的颈部，以及颈部中的凹槽，用于重新定向转子叶片中的应力。 在某些实施例中，凹槽距离至少一个接触面一定距离，其长度小于燕尾榫的长度，和/或在翼型的后缘侧具有初始非零深度，并且 在翼型的前缘方向上逐渐变细到零深度。
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公开(公告)号：US20130224036A1
公开(公告)日：2013-08-29
申请号：US13405738
申请日：2012-02-27
申请人： Olivier Jacques Louis LAMICQ , Fernando Manuel Ibarra Esparragoza , Paul Francis Norton , Jeremiah Wesley Key
发明人： Olivier Jacques Louis LAMICQ , Fernando Manuel Ibarra Esparragoza , Paul Francis Norton , Jeremiah Wesley Key
CPC分类号： F01D5/3007 , F05D2250/29 , F05D2250/712
摘要： A rotor blade for a gas turbine engine has an airfoil, a base integrally joined to the airfoil, and a root integrally joined to the base and mountable in a slot in a rotor hub of the gas turbine engine. The root has a dovetail including at least one contact face that, when mounted, contacts a surface of the slot to retain the rotor blade in the hub. The root includes a neck between the base and the dovetail, and a groove in the neck for redirecting stress in the rotor blade. In certain embodiments, the groove is at a distance from the at least one contact face, has a length less than a length of the dovetail, and/or has an initial non-zero depth at the side of a trailing edge of the airfoil and tapers to a zero depth in the direction of the leading edge of the airfoil.
摘要翻译： 用于燃气涡轮发动机的转子叶片具有翼型件，与翼型件一体地接合的基座，以及整体地连接到基座并可安装在燃气涡轮发动机的转子毂中的槽中的根部。 根部具有燕尾榫，包括至少一个接触面，当安装时，接触面接触槽的表面以将转子叶片保持在轮毂中。 根部包括在基部和燕尾榫之间的颈部，以及颈部中的凹槽，用于重新定向转子叶片中的应力。 在某些实施例中，凹槽距离至少一个接触面一定距离，其长度小于燕尾榫的长度，和/或在翼型的后缘侧具有初始非零深度，并且 在翼型的前缘方向上逐渐变细到零深度。
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