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1. 发明申请

US20130064671A1 AIRFOIL SHAPE FOR TURBINE BUCKET AND TURBINE INCORPORATING SAME 失效
标题翻译：用于涡轮缸和涡轮机的气翼形状包括在内
公开(公告)号：US20130064671A1
公开(公告)日：2013-03-14
申请号：US13229975
申请日：2011-09-12
申请人： Jason Douglas Herzlinger , Craig Allen Bielek , Jonathan Glenn Reed , Holly Renae Davis , Luis Manuel Herrera , Ariel Caesar Prepena Jacala , William Scott Zemitis
发明人： Jason Douglas Herzlinger , Craig Allen Bielek , Jonathan Glenn Reed , Holly Renae Davis , Luis Manuel Herrera , Ariel Caesar Prepena Jacala , William Scott Zemitis
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F05D2250/74
摘要： A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译：提供一种涡轮机桶，其包括具有翼型形状的铲斗翼型，铲斗翼型件具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中X，Y和Z的笛卡尔坐标值是通过将X，Y和Z的笛卡尔坐标值乘以翼型的高度（英寸），其中X和Y是以英寸为单位的距离，其中，当通过平滑连续的弧连接，在每个距离Z处限定翼型轮廓部分，Z距离处的翼型轮廓部分彼此平滑地连接以形成完整的翼型形状。

2. 发明授权

US08714930B2 Airfoil shape for turbine bucket and turbine incorporating same 失效
标题翻译：涡轮机叶片和涡轮机的翼型形成
公开(公告)号：US08714930B2
公开(公告)日：2014-05-06
申请号：US13229975
申请日：2011-09-12
申请人： Jason Douglas Herzlinger , Craig Allen Bielek , Jonathan Glenn Reed , Holly Renae Davis , Luis Manuel Herrera , Ariel Caesar Prepena Jacala , William Scott Zemitis
发明人： Jason Douglas Herzlinger , Craig Allen Bielek , Jonathan Glenn Reed , Holly Renae Davis , Luis Manuel Herrera , Ariel Caesar Prepena Jacala , William Scott Zemitis
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F05D2250/74
摘要： A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译：提供一种涡轮机桶，其包括具有翼型形状的铲斗翼型，铲斗翼型件具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中X，Y和Z的笛卡尔坐标值是通过将X，Y和Z的笛卡尔坐标值乘以翼型的高度（英寸），其中X和Y是以英寸为单位的距离，其中，当通过平滑连续的弧连接，在每个距离Z处限定翼型轮廓部分，Z距离处的翼型轮廓部分彼此平滑地连接以形成完整的翼型形状。

3. 发明授权

US08790086B2 Turbine blade assembly for retaining sealing and dampening elements 有权
标题翻译：用于保持密封和阻尼元件的涡轮叶片组件
公开(公告)号：US08790086B2
公开(公告)日：2014-07-29
申请号：US12944209
申请日：2010-11-11
申请人： Mark Steven Honkomp , Matthew Durham Collier , Jason Douglas Herzlinger
发明人： Mark Steven Honkomp , Matthew Durham Collier , Jason Douglas Herzlinger
IPC分类号： F01D5/10 , F01D5/26
CPC分类号： F01D5/22 , F01D11/006 , F05D2260/96
摘要： A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.
摘要翻译：涡轮机具有围绕转子设置的叶片组件。每个叶片组件都具有翼型和铲斗。口袋被定义在桶的尾部和前侧，其端部具有阻尼器销槽。后侧的减震器销槽具有足以完全容纳阻尼销的深度。第一相邻刀片组件的后侧的阻尼器销槽相对于第二相邻刀片组件的前侧处的阻尼器销槽定位，以允许阻尼销移动。在后侧的袋的每一侧是其中具有密封销的密封销槽。密封销槽延伸超过在后侧与减震器销槽的内边缘对齐的线，其中密封销与阻尼销重叠。

4. 发明申请

US20120121423A1 TURBINE BLADE ASSEMBLY 有权
标题翻译：涡轮叶片组件
公开(公告)号：US20120121423A1
公开(公告)日：2012-05-17
申请号：US12944209
申请日：2010-11-11
申请人： Mark Steven Honkomp , Matthew Durham Collier , Jason Douglas Herzlinger
发明人： Mark Steven Honkomp , Matthew Durham Collier , Jason Douglas Herzlinger
IPC分类号： F01D5/26
CPC分类号： F01D5/22 , F01D11/006 , F05D2260/96
摘要： A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.
摘要翻译：涡轮机具有围绕转子设置的叶片组件。每个叶片组件都具有翼型和铲斗。口袋被定义在桶的尾部和前侧，其端部具有阻尼器销槽。后侧的减震器销槽具有足以完全容纳阻尼销的深度。第一相邻刀片组件的后侧的阻尼器销槽相对于第二相邻刀片组件的前侧处的阻尼器销槽定位，以允许阻尼销移动。在后侧的袋的每一侧是其中具有密封销的密封销槽。密封销槽延伸超过在后侧与减震器销槽的内边缘对齐的线，其中密封销与阻尼销重叠。

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