公开(公告)号：US20050118023A1

公开(公告)日：2005-06-02

申请号：US10881506

申请日：2004-06-29

Applicant: Ronald Bunker ,  Ching-Pang Lee

Inventor： Ronald Bunker ,  Ching-Pang Lee

IPC: F01D9/02 ,  F01D5/18 ,  F02C7/18 ,  F28F3/02 ,  F28F3/04 ,  F28F13/12 ,  F03D11/02

CPC classification number: F28F13/12 ,  F01D5/187 ,  F05D2230/90 ,  F05D2250/28 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  F28F3/022 ,  F28F3/044 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/4932

Abstract: A component includes at least one wall having an inner portion and an outer portion. A number of pins extend between the inner and outer portions. The pins define a mesh cooling arrangement with a number of flow channels. The inner portion of the wall defines a number of dimples. A method for forming a number of cooling holes in a component is described. The component has at least one wall with inner and outer portions. The inner portion defines a number of dimples. The method includes centering a drilling tool on a dimple, drilling at least one impingement cooling hole through the inner portion of the wall at the dimple using the drilling tool, and repeating the centering and drilling steps for a number of dimples to drill a number of impingement cooling holes in the inner portion of the wall.

Abstract translation: 一个部件包括至少一个具有内部部分和外部部分的壁。 多个销在内部和外部之间延伸。 销钉定义了具有多个流动通道的网状冷却装置。 壁的内部部分限定了多个凹坑。 描述了在部件中形成多个冷却孔的方法。 该部件具有至少一个具有内部和外部部分的壁。 内部部分限定了一些凹坑。 该方法包括将钻孔工具定中在凹坑上，使用钻孔工具在凹坑处穿过壁的内部部分的至少一个冲击冷却孔钻孔，并重复多个凹坑的定中心和钻孔步骤以钻出若干个 在壁的内部的冲击冷却孔。

公开(公告)号：US20050058534A1

公开(公告)日：2005-03-17

申请号：US10664192

申请日：2003-09-17

Applicant: Ching-Pang Lee ,  Ramgopal Darolia

Inventor： Ching-Pang Lee ,  Ramgopal Darolia

IPC: F02C7/18 ,  F01D5/28 ,  F01D11/24 ,  F01D25/12 ,  F02C7/28 ,  F04D31/00

CPC classification number: F01D11/24 ,  F01D5/288 ,  F01D25/12 ,  F05D2260/204 ,  Y02T50/67 ,  Y02T50/676

Abstract: A turbine wall includes a metal substrate having front and back surfaces. A thermal barrier coating is bonded atop the front surface. A network of flow channels is laminated between the substrate and the coating for carrying an air coolant therebetween for cooling the thermal barrier coating.

Abstract translation: 涡轮壁包括具有前表面和后表面的金属基底。 隔热涂层粘结在前表面顶部。 流动通道网络层压在基板和涂层之间，用于在其间承载空气冷却剂以冷却隔热涂层。

公开(公告)号：US20050028531A1

公开(公告)日：2005-02-10

申请号：US10422314

申请日：2003-04-24

Applicant: Kattalaicheri Venkataramani ,  Lawrence Butler ,  Ching-Pang Lee ,  Harvey Maclin

Inventor： Kattalaicheri Venkataramani ,  Lawrence Butler ,  Ching-Pang Lee ,  Harvey Maclin

IPC: F02C5/04 ,  F02C5/11 ,  F02C5/12 ,  F02K3/06 ,  F02K7/06 ,  F02K7/075 ,  F23R7/00 ,  F02C5/00

CPC classification number: F02K3/06 ,  F02C5/11 ,  F02C5/12 ,  F02K7/02 ,  F05D2250/314 ,  F23R7/00

Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where a plurality of spaced detonation passages are disposed therethrough. Each detonation passage includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases exit the aft surface of the cylindrical member to create a torque which causes the cylindrical member to rotate. Each detonation passage further includes a first end located adjacent the forward surface of the cylindrical member and a second end located adjacent the aft surface of the cylindrical member.

Abstract translation: 用于具有延伸穿过其中的纵向中心线轴的燃气涡轮发动机的脉冲爆震系统包括具有前表面，后表面和外周表面的可旋转圆柱形构件，其中多个间隔开的爆震通道穿过其中。 每个爆震通道包括至少一个具有延伸穿过的纵向轴线的部分，该纵向轴线以与纵向中心线轴线成圆周方向定位。 脉冲爆震系统还包括可旋转地连接到圆柱形构件的轴和定子，其与圆柱形构件的前表面和轴的一部分间隔开地配置。 定子具有至少一组端口，当圆柱形构件旋转时，该组端口可与引爆通道对准。 以这种方式，在引爆通道中进行爆震循环，使得燃烧气体离开圆柱形构件的后表面以产生使圆柱形构件旋转的扭矩。 每个引爆通道还包括位于圆柱形构件的前表面附近的第一端和位于圆柱形构件的后表面附近的第二端。

公开(公告)号：US06838190B2

公开(公告)日：2005-01-04

申请号：US10028109

申请日：2001-12-20

Applicant: Ching-Pang Lee ,  Melvin Robert Jackson ,  Stephen Joseph Ferrigno ,  Gary Edward Trewiler ,  Mark Daniel Gorman

Inventor： Ching-Pang Lee ,  Melvin Robert Jackson ,  Stephen Joseph Ferrigno ,  Gary Edward Trewiler ,  Mark Daniel Gorman

IPC: B32B15/01 ,  C22C5/04 ,  C22C27/06 ,  B32B15/04 ,  B32B15/20 ,  B64C11/16 ,  F01D5/14

CPC classification number: B32B15/018 ,  C22C5/04 ,  C22C27/06 ,  Y10T428/1275 ,  Y10T428/12847 ,  Y10T428/12868 ,  Y10T428/12875 ,  Y10T428/12944

Abstract: A protected article includes a nickel-base superalloy substrate, an interlayer overlying the substrate, and a protective layer overlying the interlayer. The protective layer has a composition comprising at least one of rhodium, platinum, palladium, and ruthenium. In one composition, palladium is present in an amount of from about 1 to about 41 atomic percent; platinum is present in an amount of about (40+atomic percent palladium) atomic percent for palladium ranging from about 1 atomic percent to about 14 atomic percent and up to about 54 atomic percent for palladium ranging from about 15 atomic percent up to about 41 atomic percent; rhodium is present in an amount of at least about 24 atomic percent; zirconium, hafnium, titanium, and mixtures thereof are present in an amount of from zero up to about 5 atomic percent; and ruthenium is present in an amount of from zero up to about 5 atomic percent, balance impurities. The interlayer has a coefficient of thermal expansion intermediate between that of the substrate and that of the protective layer. The protected article is fabricated by furnishing the substrate, applying the interlayer over the substrate, and applying the protective layer over the interlayer. The application of the protective layer may be, for example, by welding or attachment of a solid piece.

公开(公告)号：US06832889B1

公开(公告)日：2004-12-21

申请号：US10616023

申请日：2003-07-09

Applicant: Ching-Pang Lee ,  Richard Clay Haubert ,  Harvey Michael Maclin

Inventor： Ching-Pang Lee ,  Richard Clay Haubert ,  Harvey Michael Maclin

IPC: F03D1100

CPC classification number: F01D5/20 ,  F01D5/184 ,  F01D5/186 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes a hollow airfoil integrally joined to a dovetail. The airfoil includes a perforate first bridge defining a flow channel behind the airfoil leading edge. A second bridge is spaced behind the first bridge and extends from a pressure sidewall of the airfoil short of the airfoil trailing edge. A third bridge has opposite ends joined to the pressure sidewall and the second bridge to define with the first bridge a supply channel for the leading edge channel, and defines with the second bridge a louver channel extending aft along the second bridge to its distal end at the pressure sidewall.

Abstract translation: 涡轮机叶片包括与燕尾形整体连接的中空翼片。 翼型件包括限定在翼型件前缘后面的流动通道的穿孔第一桥。 第二桥隔开在第一桥后面并且从机翼后缘的翼型的压力侧壁延伸出来。 第三桥具有连接到压力侧壁和第二桥的相对端，第一桥与第一桥形成用于前缘通道的供应通道，并且与第二桥一起限定沿着第二桥向后延伸到其远端的百叶窗通道 压力侧壁。

公开(公告)号：US06761956B2

公开(公告)日：2004-07-13

申请号：US10028108

申请日：2001-12-20

Applicant: Ching-Pang Lee ,  Robert Edwards Schafrik ,  Ramgopal Darolia

Inventor： Ching-Pang Lee ,  Robert Edwards Schafrik ,  Ramgopal Darolia

IPC: B32B310

CPC classification number: C23C28/321 ,  C23C28/3455 ,  F01D5/288 ,  F05D2230/90 ,  F05D2260/20 ,  F23R3/002 ,  F23R3/06 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T428/12361 ,  Y10T428/12479 ,  Y10T428/12611 ,  Y10T428/24273 ,  Y10T428/24322 ,  Y10T428/26

Abstract: A gas turbine engine component includes a perforate metal wall having pores extending therethrough. The wall has a first surface covered by a thermal barrier coating. The pores have first ends which are covered by the thermal barrier coating, and the pores are ventilated from an opposite second surface of the wall for cooling the thermal barrier coating.

Abstract translation: 燃气涡轮发动机部件包括具有贯穿其中延伸的孔的穿孔金属壁。 该壁具有由热障涂层覆盖的第一表面。 孔具有由热障涂层覆盖的第一端，并且孔从壁的相对的第二表面通风以冷却热障涂层。

公开(公告)号：US06743350B2

公开(公告)日：2004-06-01

申请号：US10063087

申请日：2002-03-18

Applicant: Ching-Pang Lee ,  Robert Alan Johnson ,  Bin Wei ,  Hsin-Pang Wang ,  Lawrence Bernard Kool

Inventor： Ching-Pang Lee ,  Robert Alan Johnson ,  Bin Wei ,  Hsin-Pang Wang ,  Lawrence Bernard Kool

IPC: B23H1100

CPC classification number: B23H9/16 ,  B23H9/10

Abstract: An electrode for rejuvenating a cooling passage within an airfoil, the electrode including a tip, an end, a conductive core extending between the tip and the end, and an insulating coating disposed on the conductive core. The insulating coating exposes a number of conductive strips of the conductive core extending between the tip and the end. The insulating coating forms a number of insulating portions and further exposes a number of spacer portions of the conductive core longitudinally positioned between the insulating portions. The insulating portions substantially span a distance between the tip and the end and are positioned between the conductive strips.

Abstract translation: 一种用于振动翼型内的冷却通道的电极，所述电极包括尖端，端部，在尖端和端部之间延伸的导电芯，以及设置在导电芯上的绝缘涂层。 绝缘涂层暴露出在尖端和端部之间延伸的多个导电芯的导电条。 绝缘涂层形成多个绝缘部分，并进一步暴露导体芯的多个间隔部分纵向定位在绝缘部分之间。 绝缘部分基本上跨越尖端和端部之间的距离并且位于导电条之间。

公开(公告)号：US06672829B1

公开(公告)日：2004-01-06

申请号：US10196623

申请日：2002-07-16

Applicant: David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

Inventor： David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

IPC: F01D518

CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D5/20 ,  F05D2250/292

Abstract: A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.

Abstract translation: 一种用于燃气涡轮发动机的涡轮机叶片，包括翼型件和整体式燕尾榫，用于将翼型件沿着径向轴线安装到涡轮机外罩内侧的转子盘。 所述翼型件还包括：在前缘和后缘处连接在一起的第一和第二侧壁，其中所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到顶板，用于在其上引导燃烧气体; 以及在前缘和后缘之间从顶板向外延伸的至少一个尖端肋。 尖端肋被定向成使得纵向延伸通过的轴线相对于径向轴线成一定角度，用于涡轮叶片的至少一个轴向长度的指定部分。 这种角度在指定部分可以是基本相同的，或者可以在其上变化。 因此，燃烧气体的再循环区域形成在尖端肋的远端附近，这减少了涡轮叶片至少轴向长度的指定部分的翼型和护罩之间的燃烧气体的泄漏流。

公开(公告)号：US06634860B2

公开(公告)日：2003-10-21

申请号：US10028107

申请日：2001-12-20

Applicant: Ching-Pang Lee ,  Melvin Robert Jackson ,  Stephen Joseph Ferrigno

Inventor： Ching-Pang Lee ,  Melvin Robert Jackson ,  Stephen Joseph Ferrigno

IPC: F01D518

CPC classification number: F01D5/20 ,  F01D5/18 ,  Y02T50/67 ,  Y02T50/676

Abstract: A turbine airfoil is provided having an integral tip cap and a pair of tip walls which extend radially outward past the tip cap to form a squealer tip. A coaxial pair of first and second holes extend through the tip cap and one of the tip walls respectively at an acute inclination angle, with the first hole being disposed so as to direct impingement cooling air on the tip wall having the second hole. A protective layer comprising a high temperature foil is disposed on the tip wall having the second hole therein.

公开(公告)号：US06599568B2

公开(公告)日：2003-07-29

申请号：US10247408

申请日：2002-09-19

Applicant: Ching-Pang Lee ,  Robert Edward Schafrik ,  Ramgopal Darolia

Inventor： Ching-Pang Lee ,  Robert Edward Schafrik ,  Ramgopal Darolia

IPC: B05D722

CPC classification number: F01D5/288 ,  B32B18/00 ,  B32B2311/22 ,  C04B35/111 ,  C04B35/486 ,  C04B35/488 ,  C04B37/026 ,  C04B2235/3225 ,  C04B2235/402 ,  C04B2235/404 ,  C04B2237/123 ,  C04B2237/125 ,  C04B2237/405 ,  C04B2237/62 ,  C23C28/321 ,  C23C28/3215 ,  C23C28/3455 ,  C23C28/36 ,  F01D5/183 ,  F05D2260/203 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12611 ,  Y10T428/24273 ,  Y10T428/24289 ,  Y10T428/24347 ,  Y10T428/24992 ,  Y10T428/249953 ,  Y10T428/249956 ,  Y10T428/24996

Abstract: A cooling system for cooling of the flow path surface region of an engine component used in a gas turbine engine and a method for making a system for cooling of the flow path surface region of an engine component used in a gas turbine engine. The method comprises the steps of channeling apertures in a substrate to a diameter of about 0.0005″ to about 0.02″ to allow passage of cooling fluid from a cooling fluid source; applying a bond coat of about 0.0005″ to about 0.005″ in thickness to the substrate such that the bond coat partially fills the channels; applying a porous inner TBC layer of at least about 0.01″ in thickness to the bond coat, such that the TBC fills the channels; applying an intermediate ceramic layer that is more dense than the inner TBC layer on top of the porous TBC; applying an outer TBC layer over the intermediate layer; and, passing cooling fluid from a cooling fluid source through the channel into the porous TBC. The density of thc outer TBC layer can be varied as needed to achieve desired cooling objectives. Because the channel exit is filled with porous TBC material, cooling fluid flows through the porous passageways into the inner TBC layer. Although the passageways provide a plurality of tortuous routes, the increased density of the TBC in the intermediate layer provides a resistance to flow of the cooling fluid and effectively causes the cooling fluid to more efficiently spread through the TBC in the inner layer before exiting at the outer surface.

Abstract translation: 一种用于冷却燃气涡轮发动机中使用的发动机部件的流路表面区域的冷却系统和用于制造用于燃气涡轮发动机的发动机部件的流路面区域的系统的方法。 该方法包括以下步骤：将衬底中的孔引导至约0.0005“至约0.02”的直径，以允许冷却流体从冷却流体源通过; 对基底施加厚度为约0.0005“至约0.005”的粘结层，使得粘结涂层部分填充通道; 将至少约0.01“的厚度的多孔内部TBC层施加到粘合涂层，使得TBC填充通道; 在多孔TBC的顶部施加比内部TBC层更致密的中间陶瓷层; 在所述中间层上施加外部TBC层; 并且将来自冷却流体源的冷却流体通过通道进入多孔TBC。 可以根据需要改变外部TBC层的密度以实现期望的冷却目标。 由于通道出口填充有多孔TBC材料，冷却流体流过多孔通道进入内部TBC层。 虽然通道提供了多条曲折的路线，但是TBC在中间层中的增加的密度提供了对冷却流体的流动的阻力，并有效地使冷却流体在内层中更加有效地扩散通过TBC， 外表面。