公开(公告)号：US06905309B2

公开(公告)日：2005-06-14

申请号：US10650288

申请日：2003-08-28

申请人： Jeffrey Howard Nussbaum ,  Xin Wei ,  Tara Chaidez ,  Michael Macrorie

发明人： Jeffrey Howard Nussbaum ,  Xin Wei ,  Tara Chaidez ,  Michael Macrorie

IPC分类号： F01D5/16 ,  F01D5/10 ,  F01D5/14 ,  F01D1/00

CPC分类号： F01D5/16 ,  F01D5/10 ,  F01D5/141 ,  F05D2230/11 ,  F05D2240/301 ,  F05D2250/71 ,  Y10T29/49318

摘要： A method enables a rotor blade for a gas turbine engine to be fabricated. The method comprises forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and second side walls are connected at a leading edge and at a trailing edge, and forming a winglet that extends outwardly from at least one of the airfoil first side wall and the airfoil second side wall, such that a radius extends between the winglet and at least one of the airfoil first side wall and the second side wall.

摘要翻译： 一种方法能够制造用于燃气涡轮发动机的转子叶片。 该方法包括形成包括第一侧壁和第二侧壁的翼型件，每个翼型件在翼型件根部和翼型件顶端之间沿径向跨度延伸，并且其中第一和第二侧壁在前缘和后缘连接 并且形成从所述翼型件第一侧壁和所述翼型件第二侧壁中的至少一个向外延伸的小翼，使得所述翼片与所述翼片和所述翼型件第一侧壁和所述第二侧壁中的至少一个之间延伸。

公开(公告)号：US07497664B2

公开(公告)日：2009-03-03

申请号：US11204718

申请日：2005-08-16

申请人： Robert A. Walter ,  David Christensen ,  Caroline Curtis Granda ,  Jeffrey Nussbaum ,  Anna Wei ,  Michael Macrorie ,  Tara Chaidez

发明人： Robert A. Walter ,  David Christensen ,  Caroline Curtis Granda ,  Jeffrey Nussbaum ,  Anna Wei ,  Michael Macrorie ,  Tara Chaidez

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F01D5/16 ,  F01D5/20 ,  F04D29/324 ,  Y10S416/05

摘要： Methods and apparatus for fabricating a rotor blade for a gas turbine engine are provided. The rotor blade includes an airfoil having a first sidewall and a second sidewall, connected at a leading edge and at a trailing edge. The method includes forming the airfoil portion bounded by a root portion at a zero percent radial span and a tip portion at a one hundred percent radial span, the airfoil having a radial span dependent chord length C, a respective maximum thickness T, and a maximum thickness to chord length ratio (Tmax/C ratio), forming the root portion having a first Tmax/C ratio, forming the tip portion having a second Tmax/C ratio, and forming a mid portion extending between a first radial span and a second radial span having a third Tmax/C ratio, the third Tmax/C ratio being less than the first Tmax/C ratio and the second Tmax/C ratio.

摘要翻译： 提供了一种用于制造用于燃气涡轮发动机的转子叶片的方法和装置。 转子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处连接。 该方法包括以零百分比的径向跨度形成由根部限定的翼型部分和以百分之一百的径向跨度的顶端部分，翼型件具有径向跨度依赖的弦长C，相应的最大厚度T和最大值 厚度与弦长比（Tmax / C比），形成具有第一Tmax / C比的根部，形成具有第二Tmax / C比的尖端部分，以及形成在第一径向跨度与第二径向间隔之间延伸的中间部分 具有第三Tmax / C比的径向跨度，第三Tmax / C比小于第一Tmax / C比和第二Tmax / C比。

公开(公告)号：US20070041841A1

公开(公告)日：2007-02-22

申请号：US11204718

申请日：2005-08-16

申请人： Robert Walter ,  David Christensen ,  Caroline Granda ,  Jeffrey Nussbaum ,  Anna Wei ,  Michael Macrorie ,  Tara Chaidez

发明人： Robert Walter ,  David Christensen ,  Caroline Granda ,  Jeffrey Nussbaum ,  Anna Wei ,  Michael Macrorie ,  Tara Chaidez

IPC分类号： B64C27/46

CPC分类号： F01D5/141 ,  F01D5/16 ,  F01D5/20 ,  F04D29/324 ,  Y10S416/05

摘要： Methods and apparatus for fabricating a rotor blade for a gas turbine engine are provided. The rotor blade includes an airfoil having a first sidewall and a second sidewall, connected at a leading edge and at a trailing edge. The method includes forming the airfoil portion bounded by a root portion at a zero percent radial span and a tip portion at a one hundred percent radial span, the airfoil having a radial span dependent chord length C, a respective maximum thickness T, and a maximum thickness to chord length ratio (Tmax/C ratio), forming the root portion having a first Tmax/C ratio, forming the tip portion having a second Tmax/C ratio, and forming a mid portion extending between a first radial span and a second radial span having a third Tmax/C ratio, the third Tmax/C ratio being less than the first Tmax/C ratio and the second Tmax/C ratio.

摘要翻译： 提供了一种用于制造用于燃气涡轮发动机的转子叶片的方法和装置。 转子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处连接。 该方法包括以零百分比的径向跨度形成由根部限定的翼型部分和以百分之一百的径向跨度的顶端部分，翼型件具有径向跨度依赖弦长度C，相应的最大厚度T和最大值 厚度与弦长比（T max max / C / C比），形成具有第一T最大/ C比的根部，形成具有第二T

公开(公告)号：US20050047919A1

公开(公告)日：2005-03-03

申请号：US10650288

申请日：2003-08-28

申请人： Jeffrey Nussbaum ,  Xin Wei ,  Tara Chaidez ,  Michael Macrorie

发明人： Jeffrey Nussbaum ,  Xin Wei ,  Tara Chaidez ,  Michael Macrorie

IPC分类号： F01D5/16 ,  F01D5/10 ,  F01D5/14

CPC分类号： F01D5/16 ,  F01D5/10 ,  F01D5/141 ,  F05D2230/11 ,  F05D2240/301 ,  F05D2250/71 ,  Y10T29/49318

摘要： A method enables a rotor blade for a gas turbine engine to be fabricated. The method comprises forming an airfoil including a first side wall and a second side wall that each extend in radial span between an airfoil root and an airfoil tip, and wherein the first and second side walls are connected at a leading edge and at a trailing edge, and forming a winglet that extends outwardly from at least one of the airfoil first side wall and the airfoil second side wall, such that a radius extends between the winglet and at least one of the airfoil first side wall and the second side wall.

摘要翻译： 一种方法能够制造用于燃气涡轮发动机的转子叶片。 该方法包括形成包括第一侧壁和第二侧壁的翼型件，每个翼型件在翼型件根部和翼型件顶端之间沿径向跨度延伸，并且其中第一和第二侧壁在前缘和后缘连接 并且形成从所述翼型件第一侧壁和所述翼型件第二侧壁中的至少一个向外延伸的小翼，使得所述翼片与所述翼片和所述翼型件第一侧壁和所述第二侧壁中的至少一个之间延伸。