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1. 发明授权

US07028747B2 Closed loop steam cooled airfoil 失效
公开(公告)号：US07028747B2
公开(公告)日：2006-04-18
申请号：US10308280
申请日：2002-12-03
申请人： Scott M. Widrig , Ronald J. Rudolph , Gregg P. Wagner
发明人： Scott M. Widrig , Ronald J. Rudolph , Gregg P. Wagner
IPC分类号： B22C9/10
CPC分类号： F01D5/187 , F05D2260/2214
摘要： An airfoil, a method of manufacturing an airfoil, and a system for cooling an airfoil is provided. The cooling system can be used with an airfoil located in the first stages of a combustion turbine within a combined cycle power generation plant and involves flowing closed loop steam through a pin array set within an airfoil. The airfoil can comprise a cavity having a cooling chamber bounded by an interior wall and an exterior wall so that steam can enter the cavity, pass through the pin array, and then return to the cavity to thereby cool the airfoil. The method of manufacturing an airfoil can include a type of lost wax investment casting process in which a pin array is cast into an airfoil to form a cooling chamber.

2. 发明授权

US06511293B2 Closed loop steam cooled airfoil 有权
标题翻译：闭环蒸汽冷却翼型
公开(公告)号：US06511293B2
公开(公告)日：2003-01-28
申请号：US09867166
申请日：2001-05-29
申请人： Scott M. Widrig , Ronald J. Rudolph , Gregg P. Wagner
发明人： Scott M. Widrig , Ronald J. Rudolph , Gregg P. Wagner
IPC分类号： F01D518
CPC分类号： F01D5/187 , F05D2260/2214
摘要： An airfoil, a method of manufacturing an airfoil, and a system for cooling an airfoil is provided. The cooling system can be used with an airfoil located in the first stages of a combustion turbine within a combined cycle power generation plant and involves flowing closed loop steam through a pin array set within an airfoil. The airfoil can comprise a cavity having a cooling chamber bounded by an interior wall and an exterior wall so that steam can enter the cavity, pass through the pin array, and then return to the cavity to thereby cool the airfoil. The method of manufacturing an airfoil can include a type of lost wax investment casting process in which a pin array is cast into an airfoil to form a cooling chamber.
摘要翻译：提供一种翼型件，制造翼型的方法以及用于冷却翼型的系统。冷却系统可以与位于组合循环发电厂内的燃气轮机的第一级中的翼型一起使用，并且涉及使闭环蒸汽流过设置在翼型内的销阵列。翼型件可以包括具有由内壁和外壁限定的冷却室的空腔，使得蒸汽可以进入空腔，穿过销阵列，然后返回到空腔，从而冷却翼型件。制造翼型的方法可以包括一种失蜡投资铸造工艺，其中销阵列被铸造成翼型以形成冷却室。

3. 发明申请

US20120049467A1 TURBINE BLADE SEAL ASSEMBLY 有权
标题翻译：涡轮叶片密封组件
公开(公告)号：US20120049467A1
公开(公告)日：2012-03-01
申请号：US13151363
申请日：2011-06-02
申请人： Jeffrey B. Stewart , Ronald J. Rudolph , Gennadiy Afanasiev
发明人： Jeffrey B. Stewart , Ronald J. Rudolph , Gennadiy Afanasiev
IPC分类号： F16J15/02
CPC分类号： F01D5/22 , F01D11/006 , F04D29/083
摘要： A seal assembly for an axial flow gas turbine engine includes a rotatable component having a radially extending mate face, a seal slot formed in the mate face, and a seal member slidably disposed in the seal slot. The seal slot includes a radially outer wall and an opposing radially inner wall extending into the component in a circumferential direction from the mate face. The radially outer wall is angled radially inwardly from the mate face toward an inner end portion of the seal slot. Rotation of the seal assembly during operation of the engine produces a centrifugal force on the seal member to effect movement of the seal member in the circumferential direction out of the seal slot.
摘要翻译：用于轴流式燃气涡轮发动机的密封组件包括具有径向延伸的配合面的可旋转部件，形成在配合面中的密封槽和可滑动地设置在密封槽中的密封构件。密封槽包括径向外壁和相对的径向内壁，其从配合面沿圆周方向延伸到部件中。径向外壁从配合面向密封槽的内端部径向向内成角度。在发动机操作期间，密封组件的旋转在密封构件上产生离心力，以使密封构件在圆周方向上移动离开密封槽。

4. 发明申请

US20110033312A1 COMPOUND COOLING FLOW TURBULATOR FOR TURBINE COMPONENT 有权
标题翻译：涡轮组件的复合冷却流量涡轮机
公开(公告)号：US20110033312A1
公开(公告)日：2011-02-10
申请号：US12884464
申请日：2010-09-17
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2250/181 , F05D2250/60 , F05D2250/611 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.
摘要翻译：多尺度紊流特征，包括在冷却表面（44）上的第一湍流器（46,48）和在第一湍流器上的较小湍流器（52,54,58,62）。可以在较大的湍流器（50）之间形成第一湍流器。第一个紊流器可以是交替的脊（46）和谷（48）。较小的湍流器可以是诸如凹坑（62）和凹槽（54）的凹表面特征，和/或诸如凸块（58）和较小脊（52）的凸表面特征。在脊（46）上的谷（48）和凹形湍流器（54,62）中具有凸起的湍流器（52,58）的实施例增加了冷却表面面积，减少了边界层分离，避免了冷却剂遮蔽和停滞，并且减少了部件质量

5. 发明授权

US08894367B2 Compound cooling flow turbulator for turbine component 有权
标题翻译：用于涡轮机部件的复合式冷却流动紊流器
公开(公告)号：US08894367B2
公开(公告)日：2014-11-25
申请号：US12884464
申请日：2010-09-17
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2250/181 , F05D2250/60 , F05D2250/611 , F05D2250/70 , F05D2250/711 , F05D2250/712 , F05D2260/2212 , F05D2260/22141
摘要： Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.
摘要翻译：多尺度紊流特征，包括在冷却表面（44）上的第一湍流器（46,48）和在第一湍流器上的较小湍流器（52,54,58,62）。可以在较大的湍流器（50）之间形成第一湍流器。第一个紊流器可以是交替的脊（46）和谷（48）。较小的湍流器可以是诸如凹坑（62）和凹槽（54）的凹表面特征，和/或诸如凸块（58）和较小脊（52）的凸表面特征。在脊（46）上的谷（48）和凹形湍流器（54,62）中具有凸起的湍流器（52,58）的实施例增加了冷却表面面积，减少了边界层分离，避免了冷却剂遮蔽和停滞，并且减少了部件质量

6. 发明授权

US08820754B2 Turbine blade seal assembly 有权
标题翻译：涡轮叶片密封组件
公开(公告)号：US08820754B2
公开(公告)日：2014-09-02
申请号：US13151363
申请日：2011-06-02
申请人： Jeffrey B. Stewart , Ronald J. Rudolph , Gennadiy Afanasiev
发明人： Jeffrey B. Stewart , Ronald J. Rudolph , Gennadiy Afanasiev
IPC分类号： F16J15/02 , F01D5/22 , F04D29/08 , F01D11/00
CPC分类号： F01D5/22 , F01D11/006 , F04D29/083
摘要： A seal assembly for an axial flow gas turbine engine includes a rotatable component having a radially extending mate face, a seal slot formed in the mate face, and a seal member slidably disposed in the seal slot. The seal slot includes a radially outer wall and an opposing radially inner wall extending into the component in a circumferential direction from the mate face. The radially outer wall is angled radially inwardly from the mate face toward an inner end portion of the seal slot. Rotation of the seal assembly during operation of the engine produces a centrifugal force on the seal member to effect movement of the seal member in the circumferential direction out of the seal slot.
摘要翻译：用于轴流式燃气涡轮发动机的密封组件包括具有径向延伸的配合面的可旋转部件，形成在配合面中的密封槽以及可滑动地设置在密封槽中的密封构件。密封槽包括径向外壁和相对的径向内壁，其从配合面沿圆周方向延伸到部件中。径向外壁从配合面向密封槽的内端部径向向内成角度。在发动机操作期间，密封组件的旋转在密封构件上产生离心力，以使密封构件在圆周方向上移动离开密封槽。

7. 发明授权

US09022736B2 Integrated axial and tangential serpentine cooling circuit in a turbine airfoil 有权
标题翻译：涡轮机翼中集成的轴向和切向蛇形冷却回路
公开(公告)号：US09022736B2
公开(公告)日：2015-05-05
申请号：US13027333
申请日：2011-02-15
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph , John P. Dalton
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph , John P. Dalton
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/186 , F01D5/187 , F05D2250/185 , F05D2260/2212
摘要： A continuous serpentine cooling circuit forming a progression of radial passages (44, 45, 46, 47A, 48A) between pressure and suction side walls (52, 54) in a MID region of a turbine airfoil (24). The circuit progresses first axially, then tangentially, ending in a last radial passage (48A) adjacent to the suction side (54) and not adjacent to the pressure side (52). The passages of the axial progression (44, 45, 46) may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (47A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (47A, 48A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.
摘要翻译：连续的蛇形冷却回路，形成在涡轮机翼型件（24）的MID区域中的压力和吸力侧壁（52,54）之间的径向通道（44,45,46,47A，48A）的进展。电路首先轴向前进，然后切向地结束于邻近吸力侧（54）并且不与压力侧（52）相邻的最后一个径向通道（48A）。轴向行进（44,45,46）的通道可以与翼型件的压力和吸力侧壁相邻。最后一个径向通道（47A）的下一个可以与压力侧壁相邻并且不与吸力侧壁相邻。最后两个径向通道（47A，48A）可以沿着压力和吸力侧壁分别比在宽度方向上更长，从而在这些热壁的内部提供增加的直接冷却表面积。

8. 发明申请

US20120207614A1 INTEGRATED AXIAL AND TANGENTIAL SERPENTINE COOLING CIRCUIT IN A TURBINE AIRFOIL 有权
标题翻译：涡轮机空气中的集成式轴向和螺旋式冷却回路
公开(公告)号：US20120207614A1
公开(公告)日：2012-08-16
申请号：US13027333
申请日：2011-02-15
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph , John P. Dalton
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra , Ronald J. Rudolph , John P. Dalton
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/186 , F01D5/187 , F05D2250/185 , F05D2260/2212
摘要： A continuous serpentine cooling circuit forming a progression of radial passages (44, 45, 46, 47A, 48A) between pressure and suction side walls (52, 54) in a MID region of a turbine airfoil (24). The circuit progresses first axially, then tangentially, ending in a last radial passage (48A) adjacent to the suction side (54) and not adjacent to the pressure side (52). The passages of the axial progression (44, 45, 46) may be adjacent to both the pressure and suction side walls of the airfoil. The next to last radial passage (47A) may be adjacent to the pressure side wall and not adjacent to the suction side wall. The last two radial passages (47A, 48A) may be longer along the pressure and suction side walls respectively than they are in a width direction, providing increased direct cooling surface area on the interiors of these hot walls.
摘要翻译：连续的蛇形冷却回路，形成在涡轮机翼型件（24）的MID区域中的压力和吸力侧壁（52,54）之间的径向通道（44,45,46,47A，48A）的进展。电路首先轴向前进，然后切向地结束于邻近吸力侧（54）并且不与压力侧（52）相邻的最后一个径向通道（48A）。轴向行进（44,45,46）的通道可以与翼型件的压力和吸力侧壁相邻。最后一个径向通道（47A）的下一个可以与压力侧壁相邻并且不与吸力侧壁相邻。最后两个径向通道（47A，48A）可以沿着压力和吸力侧壁分别比在宽度方向上更长，从而在这些热壁的内部提供增加的直接冷却表面积。

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