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1. 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

2. 发明授权

US08668453B2 Cooling system having reduced mass pin fins for components in a gas turbine engine 有权
标题翻译：具有减少用于燃气涡轮发动机中的部件的散热片的冷却系统
公开(公告)号：US08668453B2
公开(公告)日：2014-03-11
申请号：US13027323
申请日：2011-02-15
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra
IPC分类号： F01D5/08
CPC分类号： F01D5/187 , F05D2210/33 , F05D2240/127 , F05D2250/32 , F05D2250/70 , F05D2260/2212
摘要： A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil.
摘要翻译：公开了一种具有用于燃气涡轮发动机的具有减小质量的一个或多个销翅片的冷却系统。冷却系统可以包括限定冷却系统的至少一部分的一个或多个第一表面。销翅片可以从限定冷却系统的表面延伸并且可以具有大致平行于表面的非圆形截面，并且横截面的外表面的至少一部分形成至少四分之一圆。销翅片的下游侧可以具有空腔以减小质量，从而形成更有效的涡轮机翼型件。

3. 发明申请

US20120207591A1 COOLING SYSTEM HAVING REDUCED MASS PIN FINS FOR COMPONENTS IN A GAS TURBINE ENGINE 有权
标题翻译：具有减少燃油涡轮发动机组件的减少质量引脚的冷却系统
公开(公告)号：US20120207591A1
公开(公告)日：2012-08-16
申请号：US13027323
申请日：2011-02-15
申请人： Ching-Pang Lee , Nan Jiang , John J. Marra
发明人： Ching-Pang Lee , Nan Jiang , John J. Marra
IPC分类号： F01D5/14
CPC分类号： F01D5/187 , F05D2210/33 , F05D2240/127 , F05D2250/32 , F05D2250/70 , F05D2260/2212
摘要： A cooling system having one or more pin fins with reduced mass for a gas turbine engine is disclosed. The cooling system may include one or more first surfaces defining at least a portion of the cooling system. The pin fin may extend from the surface defining the cooling system and may have a noncircular cross-section taken generally parallel to the surface and at least part of an outer surface of the cross-section forms at least a quartercircle. A downstream side of the pin fin may have a cavity to reduce mass, thereby creating a more efficient turbine airfoil.
摘要翻译：公开了一种具有用于燃气涡轮发动机的具有减小质量的一个或多个销翅片的冷却系统。冷却系统可以包括限定冷却系统的至少一部分的一个或多个第一表面。销翅片可以从限定冷却系统的表面延伸并且可以具有大致平行于表面的非圆形截面，并且横截面的外表面的至少一部分形成至少四分之一圆。销翅片的下游侧可以具有空腔以减小质量，从而形成更有效的涡轮机翼型件。

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

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。

6. 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。

7. 发明申请

US20180318919A1 TURBINE AIRFOIL COOLING SYSTEM WITH LEADING EDGE IMPINGEMENT COOLING SYSTEM TURBINE BLADE INVESTMENT CASTING USING FILM HOLE PROTRUSIONS FOR INTEGRAL WALL THICKNESS CONTROL 审中-公开
公开(公告)号：US20180318919A1
公开(公告)日：2018-11-08
申请号：US16036611
申请日：2018-07-16
申请人： Ching-Pang Lee , Nan Jiang
发明人： Ching-Pang Lee , Nan Jiang
IPC分类号： B22D25/02 , F01D5/18 , B22C9/04 , B22C9/10 , B22C7/02 , B22D29/00 , B22C21/14 , B22C9/24
CPC分类号： B22D25/02 , B22C7/02 , B22C9/04 , B22C9/043 , B22C9/10 , B22C9/108 , B22C9/24 , B22C21/14 , B22D29/001 , F01D5/186 , F05D2220/32 , F05D2230/211
摘要： A method of forming an airfoil (12), including: abutting end faces (72) of cantilevered film hole protrusions (64) extending from a ceramic core (50) against an inner surface (80) of a wax die (68) to hold the ceramic core in a fixed positional relationship with the wax die; casting an airfoil including a superalloy around the ceramic core; and machining film cooling holes (34) in the airfoil after the casting step to form an pattern of film cooling holes comprising the film cooling holes formed by the machining step and the cast film cooling holes (102) formed by the film hole protrusions during the casting step.

8. 发明授权

US08511968B2 Turbine vane for a gas turbine engine having serpentine cooling channels with internal flow blockers 失效
标题翻译：具有蛇形冷却通道和内部阻流器的燃气涡轮发动机的涡轮叶片
公开(公告)号：US08511968B2
公开(公告)日：2013-08-20
申请号：US12540410
申请日：2009-08-13
申请人： George Liang , Nan Jiang , Zhihong Gao
发明人： George Liang , Nan Jiang , Zhihong Gao
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/126 , F05D2250/185 , F05D2260/221
摘要： A turbine vane for a gas turbine engine with an internal cooling system formed from a serpentine cooling channel with one or more flow blocking ribs is disclosed. The serpentine cooling channels may be configured to receive cooling fluids from internal cooling fluids supply channels. The serpentine cooling channels may include flow blocking ribs to form concurrent flow channels to reduce the cross-sectional area within the midchord region of the airfoil to maintain the internal through flow channel Mach number. The flow blocking ribs may include slots therein and may have any appropriate configuration. In at least one embodiment, the flow blocking ribs may be have a nonuniform taper or a uniformed taper.
摘要翻译：公开了一种具有内部冷却系统的燃气涡轮发动机的涡轮叶片，该内部冷却系统由具有一个或多个流动阻塞肋的蛇形冷却通道形成。蛇形冷却通道可以被配置为从内部冷却流体供应通道接收冷却流体。蛇形冷却通道可以包括阻流肋，以形成并流的流动通道，以减小翼型的中间区域内的横截面积，以维持内部通过流路的马赫数。流动阻塞肋可以在其中包括槽，并且可以具有任何适当的构造。在至少一个实施例中，阻流肋可以具有不均匀的锥形或均匀的锥形。

9. 发明授权

US08422197B2 Applying optical energy to nanoparticles to produce a specified nanostructure 有权
标题翻译：将光能应用于纳米颗粒以产生特定的纳米结构
公开(公告)号：US08422197B2
公开(公告)日：2013-04-16
申请号：US12836547
申请日：2010-07-14
申请人： Zvi Yaniv , Nan Jiang , James P. Novak , Richard L. Fink
发明人： Zvi Yaniv , Nan Jiang , James P. Novak , Richard L. Fink
IPC分类号： H01G9/00
CPC分类号： H01M4/1395 , B82B3/00 , B82Y30/00 , B82Y40/00 , H01G11/30 , H01G11/36 , H01G11/46 , H01M4/134 , H01M10/052 , Y02E60/13 , Y10T428/12722 , Y10T428/1275 , Y10T428/249953 , Y10T428/256 , Y10T428/26
摘要： The instant article of manufacture is made by applying optical energy to one or more layers of nanoparticulate materials under predetermined conditions to produce a nanostructure. The nanostructure has layers of optically fused nanoparticles including a predetermined pore density, a predetermined pore size, or both. The predetermined conditions for applying the optical energy may include a predetermined voltage, a predetermined duration, a predetermined power density, or combinations thereof.
摘要翻译：通过在预定条件下将光能施加到一层或多层纳米颗粒材料以制备纳米结构来制备本制品。纳米结构具有包括预定孔密度，预定孔径或两者的光学熔融纳米颗粒层。用于施加光能的预定条件可以包括预定电压，预定持续时间，预定功率密度或其组合。

10. 发明申请

US20130006028A1 CATALYTIC CRACKING APPARATUS AND PROCESS 有权
标题翻译：催化裂化装置和工艺
公开(公告)号：US20130006028A1
公开(公告)日：2013-01-03
申请号：US13503544
申请日：2010-10-29
申请人： Chaogang Xie , Yongcan Gao , Weimin Lu , Jun Long , Yan Cui , Jiushun Zhang , Yinan Yang , Jianguo Ma , Zheng Li , Nan Jiang
发明人： Chaogang Xie , Yongcan Gao , Weimin Lu , Jun Long , Yan Cui , Jiushun Zhang , Yinan Yang , Jianguo Ma , Zheng Li , Nan Jiang
IPC分类号： C07C1/20 , B01J8/24
CPC分类号： C10G51/06 , C10G11/18 , C10G11/20 , C10G51/026 , C10G2300/1014 , C10G2300/1018 , C10G2300/104 , C10G2300/301 , C10G2300/4018 , C10G2300/4093 , C10G2300/708 , C10G2400/02 , C10G2400/20
摘要： The present invention discloses catalytic cracking apparatus and process, which are useful for catalytic cracking of heavy oils with a high heavy oil conversion, a high propylene yield and low dry gas and coke yields.
摘要翻译：本发明公开了一种催化裂化装置和方法，其可用于具有高重油转化率，高丙烯产率和低干气体以及焦炭产率的重油的催化裂化。

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