公开(公告)号：US20110033312A1

公开(公告)日：2011-02-10

申请号：US12884464

申请日：2010-09-17

Applicant: Ching-Pang Lee ,  Nan Jiang ,  John J. Marra ,  Ronald J. Rudolph

Inventor： Ching-Pang Lee ,  Nan Jiang ,  John J. Marra ,  Ronald J. Rudolph

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2250/181 ,  F05D2250/60 ,  F05D2250/611 ,  F05D2250/70 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: 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.

Abstract translation: 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

公开(公告)号：US07806653B2

公开(公告)日：2010-10-05

申请号：US11615556

申请日：2006-12-22

Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

IPC: F01D9/00

CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D9/041 ,  F05D2240/301 ,  F05D2250/611 ,  F05D2250/71 ,  Y02T50/673

Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.

Abstract translation: 可用于发动机组件的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处联接到第一侧壁。 翼型件从根部径向延伸到尖端部分。 前缘和后缘中的每一个包括在根部部分和尖端部分之间限定的至少一个瘦方向改变和多个扫掠方向改变。

公开(公告)号：US07736123B2

公开(公告)日：2010-06-15

申请号：US11639878

申请日：2006-12-15

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: F01D17/20

CPC classification number: F01D5/147 ,  F01D5/145 ,  F01D9/041 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2270/172 ,  Y02T50/673 ,  Y10S415/914

Abstract: A trailing edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction, one or more spanwise extending plasma generators in a trailing edge region around a trailing edge of the airfoil. The plasma generators may be mounted on an outer wall of the airfoil with first and second pluralities of the plasma generators on pressure and suction sides of the airfoil respectively. The plasma generators may include inner and outer electrodes separated by a dielectric material disposed within a grooves in an outer hot surface of the outer wall of the airfoil. The plasma generators may be located at an aft end of the airfoil and the inner electrodes flush with the trailing edge base. A method for operating the system includes energizing one or more of plasma generators in steady state or unsteady modes.

Abstract translation: 后缘涡流减少系统包括在翼展方向上延伸的燃气涡轮发动机翼型件，在翼型件的后缘周围的后缘区域中的一个或多个翼展方向延伸的等离子体发生器。 等离子体发生器可以分别安装在机翼的外壁上，其中第一和第二多个等离子体发生器分别在翼型的压力和吸力侧。 等离子体发生器可以包括由设置在翼型件的外壁的外部热表面中的凹槽内的介电材料隔开的内部和外部电极。 等离子体发生器可以位于翼型的后端，并且内部电极与后缘基座齐平。 用于操作该系统的方法包括给稳态或不稳定模式中的一个或多个等离子体发生器通电。

公开(公告)号：US07686578B2

公开(公告)日：2010-03-30

申请号：US11507121

申请日：2006-08-21

Applicant: Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

Inventor： Kevin Samuel Klasing ,  Ching-Pang Lee ,  Paul Hadley Vitt ,  Brian David Keith

IPC: F01D5/20

CPC classification number: F01D5/20 ,  F01D5/187 ,  F05D2250/185 ,  F05D2250/70 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes an airfoil tip with first and second tip ribs extending from a tip floor. The ribs extend along the opposite pressure and suction sides of the blade and are joined together at opposite leading and trailing edges. A tip baffle is nested transversely between the ribs, and conforms with the second rib to bifurcate the airfoil tip into first and second tip pockets extending along the corresponding pressure and suction sides.

Abstract translation: 涡轮机叶片包括具有从尖端底板延伸的第一和第二末端肋的翼面末端。 肋沿刀片的相对的压力和吸力侧延伸并且在相对的前缘和后缘连接在一起。 尖端挡板横向嵌套在肋之间，并且与第二肋条一致，以使翼型件尖端分叉成沿相应的压力侧和吸力侧延伸的第一和第二尖端口袋。

公开(公告)号：US20100074745A1

公开(公告)日：2010-03-25

申请号：US12233847

申请日：2008-09-19

Applicant: Daniel Vern Jones ,  James Harvey Laflen ,  Richard William Albrecht ,  Dustin Alfred Placke ,  Ching-Pang Lee

Inventor： Daniel Vern Jones ,  James Harvey Laflen ,  Richard William Albrecht ,  Dustin Alfred Placke ,  Ching-Pang Lee

IPC: F01D9/04

CPC classification number: F01D25/246 ,  F01D11/24 ,  F05D2240/11 ,  Y02T50/671

Abstract: A turbine shroud includes a shroud hanger having an arcuate panel from which three inner hooks extend inwardly, and from which two outer hooks extend outwardly therefrom. The two outer hooks effect a statically determinate configuration of the shroud.

Abstract translation: 涡轮机罩包括具有弓形面板的护罩悬挂器，三个内钩从该拱形板向内延伸，两个外钩从其中向外延伸。 两个外钩影响护罩的静态结构。

公开(公告)号：US07628585B2

公开(公告)日：2009-12-08

申请号：US11639876

申请日：2006-12-15

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: F01D5/18

CPC classification number: F01D5/145 ,  F01D5/143 ,  F01D5/186 ,  F01D5/187 ,  F01D9/041 ,  F01D9/065 ,  F04D29/681 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2260/202 ,  F05D2270/17 ,  F05D2270/172 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S415/914

Abstract: A leading edge vortex reducing system includes a gas turbine engine airfoil extending in a spanwise direction away from an end wall, one or more plasma generators extending in the spanwise direction through a fillet between the airfoil and the end wall in a leading edge region near and around a leading edge of the airfoil and near the fillet. The plasma generators being operable for producing a plasma extending over a portion of the fillet in the leading edge region. The plasma generators may be mounted on an outer wall of the airfoil with a first portion of the plasma generators on a pressure side of the airfoil and a second portion of the plasma generators on a suction side of the airfoil. A method for operating the system includes energizing one or more plasma generators to form the plasma in steady state or unsteady modes.

Abstract translation: 前缘涡流减少系统包括沿翼展方向远离端壁延伸的燃气涡轮发动机翼型件，一个或多个等离子体发生器，其在翼展方向上延伸通过翼型件和端壁之间的圆角， 围绕机翼的前缘，靠近圆角。 等离子体发生器可操作用于产生在前缘区域中的圆角的一部分上延伸的等离子体。 等离子体发生器可以安装在翼型件的外壁上，其中等离子体发生器的第一部分在翼型的压力侧，等离子体发生器的第二部分在翼型的吸力侧。 用于操作该系统的方法包括激励一个或多个等离子体发生器以形成处于稳定状态或不稳定模式的等离子体。

公开(公告)号：US07624787B2

公开(公告)日：2009-12-01

申请号：US11567443

申请日：2006-12-06

Applicant: Ching-Pang Lee ,  Hsin-Pang Wang ,  Ram Kumar Upadhyay ,  Paul Richard Myers ,  Marc Thomas Edgar

Inventor： Ching-Pang Lee ,  Hsin-Pang Wang ,  Ram Kumar Upadhyay ,  Paul Richard Myers ,  Marc Thomas Edgar

IPC: B22C9/00 ,  B22C9/10

CPC classification number: B22C9/04 ,  B22C9/103

Abstract: A method of forming an integral casting core includes adding a disposable insert to a metal core die and disposing a slurry into the metal core die. The slurry includes ceramic particles. The method further includes firing the slurry to form a integral casting core and removing the disposable insert from the integral casting core.

Abstract translation: 一种形成整体铸造芯的方法包括将一次性插入物添加到金属芯模中并将浆料设置到金属芯模中。 浆料包括陶瓷颗粒。 该方法还包括焙烧浆料以形成一体的铸芯，并从整体铸造芯中去除一次性的插入物。

公开(公告)号：US07604453B2

公开(公告)日：2009-10-20

申请号：US11565180

申请日：2006-11-30

Applicant: Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

Inventor： Ching-Pang Lee ,  Eric Alan Estill ,  James Harvey Laflen ,  Katherine Jaynetorrence Andersen

IPC: F01D25/12

CPC classification number: F01D5/143 ,  F01D11/24 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A method for cooling a shroud segment of a gas turbine engine is provided. The method includes providing a turbine shroud assembly including a shroud segment having an inner surface and a leading edge that is substantially perpendicular to the inner surface, and coupling a turbine nozzle to the turbine shroud segment such that a gap is defined between an aft edge of an outer band of the turbine nozzle and the leading edge. The method also includes directing cooling air into the gap, circumferentially mixing the cooling air in a plenum defined within the leading edge to substantially uniformly distribute the cooling air throughout the gap, and directing the cooling air in the gap through at least one cooling hole formed between the plenum and the inner surface.

Abstract translation: 提供了一种用于冷却燃气涡轮发动机的护罩部分的方法。 该方法包括提供一种涡轮机护罩组件，其包括具有内表面和大致垂直于内表面的前缘的护罩区段，以及将涡轮喷嘴连接到涡轮机护罩区段，使得间隙限定在 涡轮喷嘴的外带和前缘。 该方法还包括将冷却空气引导到间隙中，将冷却空气周向地混合在限定在前缘内的增压室中，以将冷却空气基本上均匀地分布在整个间隙中，并且将空气中的冷却空气引导通过形成的至少一个冷却孔 在气室和内表面之间。

公开(公告)号：US07584538B2

公开(公告)日：2009-09-08

申请号：US11766509

申请日：2007-06-21

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: B23P15/02 ,  F01D5/20

CPC classification number: B23P6/007 ,  F01D5/005 ,  F01D5/20 ,  F05D2260/202 ,  Y10T29/49318 ,  Y10T29/49337 ,  Y10T29/49339 ,  Y10T29/49341 ,  Y10T29/49728 ,  Y10T29/53091

Abstract: A method of constructing a turbine blade for a gas turbine engine is provided. The method includes casting the blade, forming a plurality of spaced-apart notches in the airfoil proximate the tip on the pressure sidewall and forming at least one hole in each tip shelf communicating with the interior void of the airfoil for channeling cooling air from the interior void of the airfoil to thereby form a squealer tip.

Abstract translation: 提供了一种构造用于燃气轮机的涡轮叶片的方法。 该方法包括铸造叶片，在靠近压力侧壁上的尖端的翼型件中形成多个间隔开的凹口，并在每个尖端架中形成至少一个孔，该孔与翼型件的内部空隙连通，用于从内部引导冷却空气 翼型件无效，从而形成一个尖叫。

公开(公告)号：US07575415B2

公开(公告)日：2009-08-18

申请号：US11271101

申请日：2005-11-10

Applicant: Vincent Marion Drerup ,  Harold Ray Hansel ,  James Anthony Ketzer ,  Ching-Pang Lee

Inventor： Vincent Marion Drerup ,  Harold Ray Hansel ,  James Anthony Ketzer ,  Ching-Pang Lee

IPC: F01D9/04

CPC classification number: F02C7/28 ,  F01D11/005 ,  F05D2240/12 ,  F05D2260/30 ,  Y10T29/49297 ,  Y10T29/4932 ,  Y10T29/49323

Abstract: A method for assembling a gas turbine engine is provided. The method comprises coupling a first turbine nozzle within the engine, coupling a second turbine nozzle circumferentially adjacent the first turbine nozzle such that a gap is defined between the first and second turbine nozzles and providing at least one spline seal including a substantially planar body. The method also comprises forming at least one retainer tab to extend outward from the body portion of the at least one spline seal, and inserting the at least one spline seal into a slot defined in at least one of the first and second turbine nozzles to facilitate reducing leakage through the gap, such that the at least one retainer tab facilitates retaining the retainer tab within the turbine nozzle slot.

Abstract translation: 提供一种用于组装燃气涡轮发动机的方法。 该方法包括将第一涡轮喷嘴联接在发动机内，将第二涡轮喷嘴与第一涡轮喷嘴周向相邻地连接，使得在第一涡轮喷嘴和第二涡轮喷嘴之间限定间隙，并提供包括基本上平面的主体的至少一个花键密封。 该方法还包括形成至少一个保持器突片以从至少一个花键密封件的主体部分向外延伸，以及将至少一个花键密封件插入限定在第一和第二涡轮喷嘴中的至少一个中的狭槽中，以便于 减少通过间隙的泄漏，使得至少一个保持器翼片有助于将保持器突片保持在涡轮喷嘴槽内。