公开(公告)号：US20140338866A1

公开(公告)日：2014-11-20

申请号：US13893392

申请日：2013-05-14

Applicant: CHING-PANG LEE

Inventor： CHING-PANG LEE

IPC: F28F13/12

CPC classification number: F28F13/12 ,  F01D5/187 ,  F05D2260/22141

Abstract: A cooling passage defined between first and second spaced apart sidewalls of a turbine engine component includes a turbulator system including a plurality of rows of turbulator members. Each row includes a first side turbulator member extending from the first sidewall, and a second side turbulator member extending from the second sidewall. The first and second side turbulator members are arranged such that a space is defined therebetween. The first and second side turbulator members are staggered with respect to one another such that respective forward and aft ends thereof are offset from one another. Each row further includes at least one elongate intermediate turbulator member located at least partially in the space between the respective first and second side turbulator members.

Abstract translation: 限定在涡轮发动机部件的第一和第二间隔开的侧壁之间的冷却通道包括包括多排湍流器构件的湍流器系统。 每排包括从第一侧壁延伸的第一侧湍流器构件和从第二侧壁延伸的第二侧湍流构件。 第一和第二侧面紊流器构件被布置成使得在它们之间限定空间。 第一和第二侧面紊流器构件相对于彼此交错，使得其相应的前端和后端彼此偏移。 每列还包括至少一个至少部分地位于相应的第一和第二侧面湍流器构件之间的空间中的细长的中间湍流器构件。

公开(公告)号：US20140110559A1

公开(公告)日：2014-04-24

申请号：US13658045

申请日：2012-10-23

Applicant: CHING-PANG LEE ,  BENJAMIN E. HENEVELD

Inventor： CHING-PANG LEE ,  BENJAMIN E. HENEVELD

IPC: B22C9/10

CPC classification number: B22C9/10 ,  F01D5/186 ,  F01D5/187 ,  F05D2230/21 ,  F05D2230/211

Abstract: A ceramic casting core, including: a plurality of rows (162, 166, 168) of gaps (164), each gap (164) comprising an airfoil shape; interstitial core material (172) that defines and separates adjacent gaps (164) in each row (162, 166, 168); and connecting core material (178) that connects adjacent rows (170, 174, 176) of interstitial core material (172). Ends of interstitial core material (172) in one row (170, 174, 176) align with ends of interstitial core material (172) in an adjacent row (170, 174, 176) to form a plurality of continuous and serpentine shaped structures each comprising interstitial core material (172) from at least two adjacent rows (170, 174, 176) and connecting core material (178).

Abstract translation: 一种陶瓷铸造芯，包括：多个间隙（164）的排（162,166,168），每个间隙（164）包括翼型形状; 间隙芯材料（172），其限定和分隔每排（162,166,168）中的相邻间隙（164）; 以及连接芯材料（178），其连接间隙芯材料（172）的相邻行（170,174,176）。 一排（170,174,176）中的间隙芯材（172）的端部与相邻排（170,174,176）中的间隙芯材（172）的端部对准，以形成多个连续和蛇形形状的结构 包括来自至少两个相邻行（170,174,176）和连接芯材（178）的间隙芯材料（172）。

公开(公告)号：US20100025001A1

公开(公告)日：2010-02-04

申请号：US11767637

申请日：2007-06-25

Applicant: CHING-PANG LEE ,  Martin Kin-Fei Lee ,  Hsin-Pang Wang

Inventor： CHING-PANG LEE ,  Martin Kin-Fei Lee ,  Hsin-Pang Wang

IPC: B22C9/10

CPC classification number: B22C9/04 ,  B22C7/02 ,  B22C9/043

Abstract: Methods involving providing an integrated disposable core and shell die of an authentic gas turbine component, inserting at least one through-rod through the integrated disposable core and shell die, casting an integrated core and shell mold inside of the integrated disposable core and shell die, removing the integrated disposable core and shell die to obtain the integrated core and shell casting mold having the at least one through-rod disposed therein, casting an authentic gas turbine component replica using the integrated core and shell casting mold, and removing the integrated core and shell casting mold and the at least one through-rod to obtain the authentic gas turbine component replica.

Abstract translation: 涉及提供真正的燃气轮机部件的集成的一次性核心和壳模的方法，通过集成的一次性芯和壳模具插入至少一个通孔，在集成的一次性芯和壳模内部铸造集成的芯和壳模具， 去除集成的一次性芯壳模具以获得具有设置在其中的至少一个通孔的集成核心和壳体铸造模具，使用集成的芯和壳铸造铸造真实的燃气轮机部件副本，并且移除集成的芯和 壳铸造模具和至少一个通杆以获得正宗的燃气轮机部件复制品。

公开(公告)号：US20140112799A1

公开(公告)日：2014-04-24

申请号：US13657923

申请日：2012-10-23

Applicant: CHING-PANG LEE ,  BENJAMIN E. HENEVELD

Inventor： CHING-PANG LEE ,  BENJAMIN E. HENEVELD

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2250/185 ,  F05D2260/22141

Abstract: A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.

Abstract translation: 一种用于燃气涡轮发动机部件的冷却装置（82），所述冷却装置（82）具有多排（92,94,96）的翼型件（98），其中在一排（92,94）内相邻的翼型件 ，96）限定冷却通道（90）的段（110,130,140），并且其中一排（92,94）中的段（110,130）的出口（114,134）在空气动力学上与入口（132， 142）在相邻排（94,96）中的段（130,140）中以限定具有非连续壁（116,120）的连续冷却通道（90），每个冷却通道（90）包括蛇形形状。

公开(公告)号：US20130302166A1

公开(公告)日：2013-11-14

申请号：US13467112

申请日：2012-05-09

Applicant: CHING-PANG LEE ,  Mrinal Munshi

Inventor： CHING-PANG LEE ,  Mrinal Munshi

IPC: F01D5/08 ,  B23K31/02

CPC classification number: B23P6/002 ,  F01D5/005 ,  F01D5/18 ,  F01D5/20 ,  F01D11/14

Abstract: A squealer tip usable in repair systems and formed from a pressure side outer weld rib and a suction side outer weld rib extending radially outward from a tip of the turbine blade and resting upon pressure side and suction side weld members separated by a mid-chord member is disclosed. The pressure and suction side outer weld ribs may be positioned along the pressure side and the suction side of the turbine blade, respectively. The pressure side outer weld rib may include a chamfered pressure side with film cooling holes having exhaust outlets positioned therein. The pressure and suction side weld members may be configured to retain the mid-chord member in position with over extending side surfaces.

Abstract translation: 一种可用于修理系统的起重机末端，由压力侧外部焊接肋和从涡轮机叶片的顶端径向向外延伸的吸入侧外部焊接肋形成，并位于压力侧，并且由中间弦构件分隔的吸入侧焊接构件 被披露。 压力和吸力侧外部焊接肋可以分别沿涡轮叶片的压力侧和吸力侧定位。 压力侧外部焊接肋可以包括倒角压力侧，其中具有定位在其中的排气出口的膜冷却孔。 压力和吸力侧焊接构件可以构造成将中弦构件保持在适当位置并且具有过度延伸的侧表面。