公开(公告)号：US08667682B2

公开(公告)日：2014-03-11

申请号：US13094966

申请日：2011-04-27

Applicant: Ching-Pang Lee ,  Jay A. Morrison

Inventor： Ching-Pang Lee ,  Jay A. Morrison

IPC: B21D53/00

CPC classification number: B21K3/00 ,  F01D9/023 ,  F05D2260/201 ,  F23R3/425 ,  F23R3/46

Abstract: A method of forming an internal combustion engine component having a multi-panel outer wall. The multi-panel outer wall has an inner panel (16) with an inner surface (18) and an outer surface (37). The inner panel outer surface (37) has discrete pockets (23) formed by integral structural ribs (38). Each pocket (23) has a film cooling hole (31) between the pocket (23) and the plenum (20). The method includes: forming dimples (40) in the intermediate panel (22), at least one dimple (40) having a nozzle (29); securing the intermediate panel (22) to the inner panel outer surface (37), thereby enclosing at least one pocket (23); and ensuring a respective dimple (40) having a nozzle (29) protrudes into a respective enclosed pocket (24) and a respective nozzle (29) is configured to direct a respective jet (35) of cooling fluid onto the inner panel outer surface within the respective enclosed pocket (23).

Abstract translation: 一种形成具有多面板外壁的内燃机部件的方法。 多面板外壁具有带有内表面（18）和外表面（37）的内板（16）。 内板外表面（37）具有由整体结构肋（38）形成的分立的袋（23）。 每个袋（23）在袋（23）和集气室（20）之间具有膜冷却孔（31）。 该方法包括：在中间板（22）中形成凹坑（40），至少一个具有喷嘴（29）的凹坑（40）; 将所述中间板（22）固定到所述内板外表面（37）上，从而封闭至少一个凹槽（23）; 并且确保具有喷嘴（29）的相应的凹坑（40）突出到相应的封闭的袋（24）中，并且相应的喷嘴（29）构造成将相应的冷却流体喷射（35）引导到内板的外表面 相应的封闭口袋（23）。

公开(公告)号：US08647067B2

公开(公告)日：2014-02-11

申请号：US12330783

申请日：2008-12-09

Applicant: Vidhu Shekhar Pandey ,  Jeffrey Donald Clements ,  Ching-Pang Lee

Inventor： Vidhu Shekhar Pandey ,  Jeffrey Donald Clements ,  Ching-Pang Lee

IPC: B63H1/26 ,  B63H1/16

CPC classification number: F01D5/145 ,  F01D5/143 ,  Y02T50/673

Abstract: A turbine blade includes an airfoil and integral platform at the root thereof. The platform is contoured in elevation from a bank adjacent the pressure side of the airfoil to a trough commencing behind the airfoil leading edge.

Abstract translation: 涡轮机叶片包括在其根部处的翼型件和整体式平台。 平台的高度是从靠近翼型的压力侧的一个堤岸到从翼型前缘的后面开始的槽。

公开(公告)号：US20140037461A1

公开(公告)日：2014-02-06

申请号：US14048074

申请日：2013-10-08

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2260/202

Abstract: An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, a plurality of cooling fluid passages, and a plurality of radial passageways. The outer wall has leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall and receives cooling fluid for cooling the outer wall. The cooling fluid passages are in fluid communication with the cooling fluid cavity and include alternating angled sections, each section having both a radial component and a chordal component. The cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall and receive cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge. The radial passageways interconnect radially adjacent cooling fluid passages.

Abstract translation: 燃气涡轮发动机中的翼型件包括外壁，冷却流体腔，多个冷却流体通道和多个径向通道。 外壁具有前缘和后缘，压力和吸力侧以及径向内外端。 冷却流体腔被限定在外壁中并且接收用于冷却外壁的冷却流体。 冷却流体通道与冷却流体腔流体连通，并且包括交替成角度的部分，每个部分都具有径向分量和弦状分量。 冷却流体通道从冷却流体腔朝向外壁的后缘延伸，并接收来自冷却流体腔的冷却流体，用于冷却靠近后缘的外壁。 径向通道将径向相邻的冷却流体通道相互连接。

公开(公告)号：US08632311B2

公开(公告)日：2014-01-21

申请号：US11507119

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: F01D5/14

CPC classification number: F01D5/20 ,  F05D2250/712 ,  Y02T50/673

Abstract: A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.

Abstract translation: 涡轮叶片包括终止在尖端中的翼型件。 尖端包括符合翼型件的凹入压力侧的第一肋条和与翼型件的凸形吸入侧相一致的第二肋条。 第二肋从吸力侧向外张开。

公开(公告)号：US20130298400A1

公开(公告)日：2013-11-14

申请号：US13467298

申请日：2012-05-09

Applicant: Mrinal Munshi ,  Ching-Pang Lee ,  Benjamin P. Swanson ,  Petya M. Georgieva ,  James A. Morin

Inventor： Mrinal Munshi ,  Ching-Pang Lee ,  Benjamin P. Swanson ,  Petya M. Georgieva ,  James A. Morin

IPC: B23P6/00

CPC classification number: B23P6/002 ,  F01D5/005 ,  F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F01D5/20 ,  F01D11/14 ,  Y10T29/49318

Abstract: A method of repairing a turbine blade having a radially extending outer wall defining an internal cavity width and a blade tip. The method comprises removing at least a portion of the blade tip to form a repair surface and providing a tip cap having a radially outer side with an outer width that may be less than the internal cavity width, and having a radially inner side with an inner width that is substantially equal to or greater than the internal cavity width. The tip cap is positioned at the repair surface, and the tip cap is welded to the repair surface using a ductile welding material. A cap peripheral portion is formed by build-up welding around the tip cap, and a squealer portion is formed by build-up welding on the cap peripheral portion.

Abstract translation: 一种修复具有限定内腔宽度的径向延伸的外壁和叶片尖端的涡轮叶片的方法。 该方法包括去除叶片尖端的至少一部分以形成修复表面并且提供具有径向外侧的顶端帽，其外部宽度可以小于内部空腔宽度，并且具有径向内侧，内侧具有内部 宽度基本上等于或大于内腔宽度。 顶盖位于修复表面，并且使用延性焊接材料将尖端焊接到修复表面。 通过围绕尖端盖进行堆积焊接而形成盖周边部分，并且通过在盖周边部分上堆积焊接形成尖叫部分。

公开(公告)号：US20130294898A1

公开(公告)日：2013-11-07

申请号：US13463892

申请日：2012-05-04

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D25/12

CPC classification number: F01D25/12 ,  F01D5/186 ,  F05D2260/202 ,  F05D2260/204

Abstract: A component wall in a turbine engine includes a substrate and at least one cooling passage that extends through the substrate for delivering cooling fluid from a chamber associated with an inner surface of the substrate to an outer surface of the substrate. Each cooling passage is divided into at least two branches that receive cooling fluid from an entrance portion of the cooling passage that is in communication with the chamber. The branches each include an intermediate portion that extends transversely from the entrance portion and that receives cooling fluid from the entrance portion, and an exit portion that extends transversely from the respective intermediate portion. The exit portions receive the cooling fluid from the intermediate portions and deliver the cooling fluid out of the respective branch through exit portion outlets.

Abstract translation: 涡轮发动机中的部件壁包括基板和延伸穿过基板的至少一个冷却通道，用于将冷却流体从与基板的内表面相关联的室输送到基板的外表面。 每个冷却通道被分成至少两个分支，其从与冷却通道连通的冷却通道的入口部分接收冷却流体。 这些分支各自包括从入口部分横向延伸并从入口部分接收冷却流体的中间部分和从各个中间部分横向延伸的出口部分。 出口部分从中间部分接收冷却流体，并将冷却流体通过出口部分出口输送出相应分支。

公开(公告)号：US08535006B2

公开(公告)日：2013-09-17

申请号：US12836060

申请日：2010-07-14

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D25/12 ,  F01D5/187 ,  F05D2250/185 ,  F05D2260/202 ,  F05D2260/22141

Abstract: A serpentine coolant flow path (54A-54G) formed by inner walls (50, 52) in a cavity (49) between pressure and suction side walls (22, 24) of a turbine airfoil (20A). A coolant flow (58) enters (56) an end of the airfoil, flows into a span-wise channel (54A), then flows forward (54B) over the inner surface of the pressure side wall, then turns behind the leading edge (26), and flows back along a forward part of the suction side wall, then follows a loop (54E) forward and back around an inner wall (52), then flows along an intermediate part of the suction side wall, then flows into an aft channel (54G) between the pressure and suction side walls, then exits the trailing edge (28). This provides cooling matched to the heating topography of the airfoil, minimizes differential thermal expansion, revives the coolant, and minimizes the flow volume needed.

Abstract translation: 由涡轮机翼（20A）的压力侧和吸力侧壁（22,24）之间的空腔（49）中的内壁（50,52）形成的蛇形冷却剂流动路径（54A-54G）。 冷却剂流（58）进入（56）翼型件的端部，流入跨度通道（54A），然后在压力侧壁的内表面上向前（54B）流动，然后在前缘 26），并且沿吸力侧壁的前部流回，然后围绕内壁（52）向前和向后循环（54E），然后沿着吸力侧壁的中间部分流动，然后流入 在压力侧和吸力侧壁之间的后通道（54G），然后离开后缘（28）。 这提供了与翼型件的加热形状相匹配的冷却，最小化差异热膨胀，恢复冷却剂，并最小化所需的流量。

公开(公告)号：US20130149169A1

公开(公告)日：2013-06-13

申请号：US13760107

申请日：2013-02-06

Applicant: Christian X. Campbell ,  Ching-Pang Lee

Inventor： Christian X. Campbell ,  Ching-Pang Lee

IPC: F01D5/18 ,  F01D25/12

CPC classification number: F01D5/183 ,  F01D5/147 ,  F01D5/187 ,  F01D25/12 ,  F05D2240/304 ,  F05D2250/13 ,  F05D2260/2214 ,  F28F3/048 ,  F28F7/02

Abstract: A cooling channel (36, 36B, 63-66) cools inner surfaces (48, 50) of exterior walls (41, 43) of a component (20, 60). Interior side surfaces (52, 54) of the channel converge to a waist (W2), forming an hourglass shaped transverse profile (46). The inner surfaces (48, 50) may have fins (44) aligned with the coolant flow (22). The fins may have a transverse profile (56A, 56B) highest at mid-width of the inner surfaces (48, 50). Turbulators (92) may be provided on the side surfaces (52, 54) of the channel, and may urge the coolant flow toward the inner surfaces (48, 50). Each turbulator (92) may have a peak (97) that defines the waist of the cooling channel. Each turbulator may have a convex upstream side (93). These elements increase coolant flow in the corners (C) of the channel to more uniformly and efficiently cool the exterior walls (41, 43).

Abstract translation: 冷却通道（36,36B，63-66）冷却部件（20,60）的外壁（41,43）的内表面（48,50）。 通道的内侧表面（52,54）会聚到腰部（W2），形成沙漏形的横向轮廓（46）。 内表面（48,50）可具有与冷却剂流（22）对准的翅片（44）。 翅片可以具有在内表面（48,50）的中间宽度处最高的横向轮廓（56A，56B）。 紊流器（92）可以设置在通道的侧表面（52,54）上，并且可以促使冷却剂流向内表面（48,50）。 每个湍流器（92）可以具有限定冷却通道的腰部的峰（97）。 每个湍流器可以具有凸起的上游侧（93）。 这些元件增加通道的角部（C）中的冷却剂流动，以更均匀且有效地冷却外壁（41,43）。

公开(公告)号：US20130142666A1

公开(公告)日：2013-06-06

申请号：US13311630

申请日：2011-12-06

Applicant: Ching-Pang Lee ,  Glenn E. Brown ,  Benjamin E. Heneveld

Inventor： Ching-Pang Lee ,  Glenn E. Brown ,  Benjamin E. Heneveld

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/122 ,  F05D2240/304

Abstract: A turbine blade (10) including an airfoil (12) having multiple interior wall portions (70) each separating at least one chamber from another one of multiple chambers (46, 48, 50, 58, 60). In one embodiment a first wall portion (70-2) between first and second chambers (60, 52) includes first and second pluralities of flow paths (86P, 86S) extending through the first wall portion. The first wall portion includes a first region R1 having a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening (78) in the first chamber (60), through the first region and to an exit opening (82) in the second chamber (52) which path distance is greater than the first thickness.

Abstract translation: 一种涡轮机叶片（10），包括具有多个内壁部分（70）的翼型件（12），每个内壁部分（70）将至少一个腔室与多个腔室（46,48,50,58,60）中的另一个分隔开。 在一个实施例中，第一和第二腔室（60,52）之间的第一壁部分（70-2）包括延伸穿过第一壁部分的第一和第二多个流动路径（86P，86S）。 第一壁部分包括具有第一厚度t的第一区域R1，其可测量为腔室之间的距离。 路径中的一个沿着第一腔室（60）中的相关联的路径开口（78）测量的第一路径距离（d）延伸穿过第一区域并延伸到第二腔室（52）中的出口开口（82） 路径距离大于第一厚度。

公开(公告)号：US20130058756A1

公开(公告)日：2013-03-07

申请号：US13226547

申请日：2011-09-07

Applicant: Kok-Mun THAM ,  Ching-Pang LEE ,  Abdullatif M. CHEHAB ,  Gm Salam AZAD ,  Shantanu P. MHETRAS ,  Manjit SHIVANAND ,  Vincent P. LAURELLO ,  Christopher RAWLINGS

Inventor： Kok-Mun THAM ,  Ching-Pang LEE ,  Abdullatif M. CHEHAB ,  Gm Salam AZAD ,  Shantanu P. MHETRAS ,  Manjit SHIVANAND ,  Vincent P. LAURELLO ,  Christopher RAWLINGS

IPC: F04D29/58 ,  F01D1/02

CPC classification number: F01D11/001 ,  F01D11/04

Abstract: A gas turbine having rotor discs (9), a disc cavity (13) and a stator stage (25) extending to the disc cavity (13). Seal housing flanges (43, 44) extend from a seal housing (29) of the stator stage (25). Rotor flanges (41i, 41o) extend from a rotor disk (9-1). An inner rotor flange (41i) and first seal housing flange (43) are inward from a second seal housing flange (44). One rotor flange (41o) is outward from the second seal housing flange (44). The inner rotor flange (41i) and first seal housing flange (43) extend toward one another to limit movement of main gas flow (17). An inlet (47) injects air (50) between the outward rotor flange (41o) and second seal housing flange (44).

Abstract translation: 一种具有转子盘（9），延伸到盘腔（13）的盘腔（13）和定子级（25）的燃气轮机。 密封壳体凸缘（43,44）从定子台（25）的密封壳体（29）延伸。 转子凸缘（41i，41o）从转子盘（9-1）延伸。 内转子凸缘（41i）和第一密封壳体凸缘（43）从第二密封壳体凸缘（44）向内。 一个转子凸缘（41o）从第二密封壳体凸缘（44）向外。 内转子凸缘（41i）和第一密封壳体凸缘（43）朝向彼此延伸以限制主气流（17）的移动。 入口（47）在外转子凸缘（41o）和第二密封壳体凸缘（44）之间注入空气（50）。