公开(公告)号：US06461107B1

公开(公告)日：2002-10-08

申请号：US09818312

申请日：2001-03-27

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

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

IPC: F01D518

CPC classification number: F01D5/288 ,  F01D5/183 ,  F01D5/187 ,  F01D5/20 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/49318

Abstract: The present invention provides for cooling the squealer tip region of a high pressure turbine blade used in a gas turbine engine comprising coating the squealer tip with a metallic bond coat. Micro grooves oriented in the radial direction are fabricated into the airfoil on the interior surface of the squealer tip above and substantially perpendicular to the tip cap. A micro groove oriented in the axial direction is fabricated along the joint corner between the squealer tip side wall and the, tip cap to connect and act as a plenum with all of the micro grooves oriented in the radial direction. Tip cap cooling holes are drilled through the tip cap and connected to the micro groove that ultimately forms a plenum. TBC ceramic is then deposited on both blade external surfaces and the tip cavity, forming micro channels from micro grooves as a result of self shadowing. In this manner, cooling fluid passes from a cooling fluid source through the tip cap holes and into the plenum created by the micro channel, subsequently passing into the micro channels that are oriented in the radial direction. Cooling fluid is thereby directed through the micro channels to cool the squealer, exiting in the vicinity of the tip. Since the TBC is porous, some of the cooling fluid will also flow through the TBC to provide transpiration cooling. The present invention further comprises both the cooled blade and squealer tip region formed by the foregoing methods and the blade and squealer tip with the micro channels for cooling the squealer tip.

Abstract translation: 本发明提供了用于冷却在燃气涡轮发动机中使用的高压涡轮机叶片的鸣响器尖端区域，其包括用金属粘结涂层涂覆尖叫尖端。 在径向方向上定向的微槽在尖端顶部的内表面上被制造成位于尖端顶部的内表面上且基本上垂直于顶盖。 沿着轴向定向的微槽沿着尖叫尖端侧壁和尖端盖之间的接合角制造，以连接并充当具有沿径向方向定向的所有微槽的集气室。 顶盖冷却孔穿过尖端盖并连接到最终形成增压室的微槽。 然后将TBC陶瓷沉积在两个叶片外表面和尖端腔上，由于自身阴影而从微槽形成微通道。 以这种方式，冷却流体从冷却流体源通过顶盖孔并进入由微通道产生的增压室，随后进入沿径向定向的微通道。 因此，冷却流体被引导通过微通道，以冷却在尖端附近离开的鸣叫器。 由于TBC是多孔的，一些冷却流体也将流经TBC以提供蒸发冷却。 本发明还包括通过上述方法形成的冷却刀片和鸣响器尖端区域以及具有用于冷却鸣叫器尖端的微通道的刀片和尖叫尖端。

公开(公告)号：US06416283B1

公开(公告)日：2002-07-09

申请号：US09688579

申请日：2000-10-16

Applicant: Robert A. Johnson ,  Ching-Pang Lee ,  Bin Wei ,  Hsin-Pang Wang

Inventor： Robert A. Johnson ,  Ching-Pang Lee ,  Bin Wei ,  Hsin-Pang Wang

IPC: F01D508

CPC classification number: B23H1/04 ,  B23H9/10 ,  B23H9/14 ,  F05B2260/222

Abstract: An electrode having a dielectric coating is patterned to provide axially spaced rows of insulating material on the external surface of the electrode with one or more gaps in the insulating material of each row. The electrode is placed in a preformed hole of a turbine bucket and an electrolyte is provided for flow between the electrode and the walls of the hole. Upon application of an electrical current, portions of the material of the interior wall surface directly opposite the non-insulated portions of the electrode are dissolved, forming grooves. The insulated portions of the electrode leave axially spaced rows of projections extending toward the axis of the hole. The gaps in the rows or projections are axially misaligned. The projections form turbulators in the cooling flow passages of the bucket, enhancing the heat transfer coefficient.

Abstract translation: 具有电介质涂层的电极被图案化以在电极的外表面上提供轴向隔开的一排绝缘材料，其中每行的绝缘材料中具有一个或多个间隙。 将电极放置在涡轮机桶的预制孔中，并且提供电解质以在电极和孔的壁之间流动。 在施加电流时，直接与电极的非绝缘部分相对的内壁表面的材料部分被溶解，形成凹槽。 电极的绝缘部分沿着孔的轴线离开轴向间隔开的一列突起。 行或突起中的间隙轴向不对准。 这些突起在铲斗的冷却流动通道中形成涡轮，提高了传热系数。

公开(公告)号：US06413578B1

公开(公告)日：2002-07-02

申请号：US09687721

申请日：2000-10-12

Applicant: William R. Stowell ,  Robert A. Johnson ,  Andrew J. Skoog ,  Joseph Thomas Begovich ,  Thomas Walter Rentz ,  Jane Ann Murphy ,  Ching-Pang Lee ,  Dainel P. Ivkovich, Jr.

Inventor： William R. Stowell ,  Robert A. Johnson ,  Andrew J. Skoog ,  Joseph Thomas Begovich ,  Thomas Walter Rentz ,  Jane Ann Murphy ,  Ching-Pang Lee ,  Dainel P. Ivkovich, Jr.

IPC: B05D106

CPC classification number: C23C24/08 ,  Y02T50/67 ,  Y10T428/20 ,  Y10T428/24479 ,  Y10T428/24521 ,  Y10T428/25 ,  Y10T428/252

Abstract: A method of repairing a thermal barrier coating on a component designed for use in a hostile thermal environment, such as turbine, combustor and augmentor components of a gas turbine engine. The method more particularly involves repairing a thermal barrier coating on a component that has suffered localized spallation of the thermal barrier coating. After cleaning the surface area of the component exposed by the localized spallation, a ceramic paste comprising a ceramic powder in a binder is applied to the surface area of the component. The binder is then reacted to yield a ceramic-containing repair coating that covers the surface area of the component and comprises the ceramic powder in a matrix of a material formed when the binder was reacted. The binder is preferably a ceramic precursor material that can be converted immediately to a ceramic or allowed to thermally decompose over time to form a ceramic, such that the repair coating has a ceramic matrix. The repair method can be performed while the component remains installed, e.g., in a gas turbine engine. Immediately after the reaction step, the gas turbine engine can resume operation during which the binder is further reacted/converted and the strength of the repair coating increases.

Abstract translation: 在设计用于恶劣热环境中的部件（例如燃气涡轮发动机的涡轮机，燃烧器和增压器部件）上修复热障涂层的方法。 该方法更具体地涉及在已经遭受热障涂层的局部剥落的部件上修复热障涂层。 在清洁通过局部剥离暴露的部件的表面积之后，将包含粘合剂中的陶瓷粉末的陶瓷膏施加到部件的表面区域。 然后使粘合剂反应以产生覆盖部件的表面积的含陶瓷的修补涂层，并且包含当粘合剂反应时形成的材料的基质中的陶瓷粉末。 粘合剂优选是陶瓷前体材料，其可以立即转化成陶瓷或随时间而热分解形成陶瓷，使得修补涂层具有陶瓷基体。 当部件保持安装时，例如在燃气涡轮发动机中，可以执行修理方法。 在反应步骤之后，燃气涡轮发动机可以立即恢复操作，在此期间粘合剂进一步反应/转化，并且修复涂层的强度增加。

公开(公告)号：US06341939B1

公开(公告)日：2002-01-29

申请号：US09628152

申请日：2000-07-31

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D518

CPC classification number: F01D25/12 ,  F01D5/18 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes an integral airfoil, platform, shank, and dovetail, with a pair of holes in tandem extending through the platform and shank in series flow communication with an airflow channel inside the shank. Cooling air discharged through the tandem holes effects multiple, convection, impingement, and film cooling using the same air.

Abstract translation: 涡轮机叶片包括整体的翼型件，平台，柄和燕尾榫，其中一对孔串联延伸穿过平台并且与柄内的气流通道串联地流动连通。 通过串联孔排出的冷却空气使用相同的空气进行多次，对流，冲击和薄膜冷却。

公开(公告)号：US06243948B1

公开(公告)日：2001-06-12

申请号：US09443132

申请日：1999-11-18

Applicant: Ching-Pang Lee ,  Robert A. Johnson ,  Nesim Abuaf

Inventor： Ching-Pang Lee ,  Robert A. Johnson ,  Nesim Abuaf

IPC: B23P1500

CPC classification number: F01D5/186 ,  B23K26/389 ,  B23P6/002 ,  B23P2700/06 ,  F01D5/005 ,  F05D2230/10 ,  F05D2230/80 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T29/49318 ,  Y10T29/49341 ,  Y10T29/49725 ,  Y10T29/49726

Abstract: A method for modifying cooling holes in a gas turbine engine film-cooled component by machining cooling hole outlets to enlarge the outlets and remove any portion of the cooling hole walls which might exhibit cracks.

Abstract translation: 一种用于通过加工冷却孔出口来改变燃气涡轮发动机膜冷却部件中的冷却孔的方法，以扩大出口并去除可能发生裂纹的冷却孔壁的任何部分。

公开(公告)号：US06220817B1

公开(公告)日：2001-04-24

申请号：US08971305

申请日：1997-11-17

Applicant: George A. Durgin ,  Ching-Pang Lee

Inventor： George A. Durgin ,  Ching-Pang Lee

IPC: F01D508

CPC classification number: F01D5/187 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine airfoil includes a plurality of internal ribs defining at least two independent serpentine cooling circuits having outer and inner serpentine portions, respectively, in different longitudinal tiers with the outer serpentine position being disposed longitudinally above the inner tier serpentine position for differentially longitudinally cooling the airfoil. The outer and inner serpentine portions include outer and inner exits and entrances wherein the outer and inner exits are positioned aft of the outer and inner entrances, respectively, so as to have a chordal flow direction aftwards from the leading edge to the trailing edge within the serpentine portions.

Abstract translation: 涡轮机翼片包括多个内部肋条，其限定至少两个独立的蛇形冷却回路，分别在不同的纵向层中具有外部和内部蛇形部分，其中外部蛇形位置纵向设置在内部蛇形位置上方，用于差异地纵向冷却翼型件 。 外部和内部蛇形部分包括外部和外部出口和入口，其中外部出口和内部出口分别位于外部入口和内部入口的后方，以便在内部出口和内部出口之间具有从前缘到后缘的弦向流动方向 蛇纹石部分。

公开(公告)号：US6086328A

公开(公告)日：2000-07-11

申请号：US217105

申请日：1998-12-21

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  F01D5/20 ,  F01D11/08 ,  F01D5/28

CPC classification number: F01D5/18 ,  F01D5/20 ,  F05D2250/292

Abstract: A turbine blade includes a hollow airfoil extending from an integral dovetail. The airfoil includes sidewalls extending between leading and trailing edges and longitudinally between a root and a tip. The sidewalls are spaced apart to define a flow channel for channeling cooling air through the airfoil. The tip is tapered longitudinally above at least one of the sidewalls and decreases in thickness.

Abstract translation: 涡轮机叶片包括从整体燕尾形延伸的中空翼型件。 翼型件包括在前缘和后缘之间延伸的侧壁，并且在根部和尖端之间纵向延伸。 侧壁间隔开以限定用于将冷却空气引导通过翼型的流动通道。 尖端在纵向上至少一个侧壁上倾斜并且厚度减小。

公开(公告)号：US5927946A

公开(公告)日：1999-07-27

申请号：US939761

申请日：1997-09-29

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  F01D5/20

CPC classification number: F01D5/187 ,  F01D5/20

Abstract: A gas turbine engine rotor blade includes an airfoil having a concave side wall and a convex side wall joined together at leading and trailing edges. Concave and convex tip walls extend from adjacent the leading edge along the respective concave and convex side walls to adjacent the trailing edge and are spaced apart to define a tip cavity therebetween. A hole or channel is disposed in a trailing edge tip region connecting the tip cavity to the trailing edge for channeling cooling fluid through the trailing edge tip region.

Abstract translation: 燃气涡轮发动机转子叶片包括具有在前缘和后缘处连接在一起的凹侧壁和凸侧壁的翼型件。 凹凸尖端壁从相邻的凹凸侧壁的前缘相邻延伸，与后缘相邻并且间隔开以在其间限定尖端腔。 孔或通道设置在将尖端空腔连接到后缘的后缘尖端区域中，用于将冷却流体引导通过后缘尖端区域。

公开(公告)号：US5738489A

公开(公告)日：1998-04-14

申请号：US778565

申请日：1997-01-03

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18 ,  F01D25/14

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2240/81 ,  F05D2260/221

Abstract: A turbine blade includes a dovetail, shank, platform, and airfoil. A cooling circuit extends radially therethrough for circulating a coolant. A thermal conductor is disposed on a lower surface of the platform for conducting heat from the platform to the shank for removal by the coolant in the cooling circuit.

Abstract translation: 涡轮叶片包括燕尾，柄，平台和翼型件。 冷却回路径向延伸穿过其中以使冷却剂循环。 热导体设置在平台的下表面上，用于将热量从平台传导到柄部，以便由冷却回路中的冷却剂除去。

公开(公告)号：US5733102A

公开(公告)日：1998-03-31

申请号：US767905

申请日：1996-12-17

Applicant: Ching-Pang Lee ,  Gulcharan S. Brainch ,  Anne M. Isburgh

Inventor： Ching-Pang Lee ,  Gulcharan S. Brainch ,  Anne M. Isburgh

IPC: F01D5/18 ,  F01D5/20 ,  F01D5/28 ,  F01D11/12 ,  F02C7/18

CPC classification number: F01D5/288 ,  F01D11/122 ,  F01D5/187 ,  F01D5/20 ,  F05D2230/90

Abstract: A turbine blade includes an airfoil having an internal cooling circuit therein. The airfoil extends from a root to a tip cap, and includes laterally opposite pressure and suction sides extending between a leading edge and an opposite trailing edge over which is flowable a combustion gas. A pair of squealer tips extend radially upwardly from the tip cap along the pressure and suction sides, and are spaced apart between the leading and trailing edges to define an upwardly open tip cavity. At least one of the squealer tips includes a slot extending radially inwardly to the tip cap, with the slot also extending along the squealer tip between the leading and trailing edges. A plurality of spaced apart supply holes extend radially through the tip cap in the slot in flow communication with the cooling circuit for channeling the coolant into the slot for cooling the squealer tip. A thermal barrier coating may then be disposed on an outboard side of the squealer tip for providing insulation against the combustion gas flowable therealong.

Abstract translation: 涡轮叶片包括其中具有内部冷却回路的翼型件。 翼型件从根部延伸到尖端盖，并且包括在前缘和相对的后缘之间延伸的横向相对的压力和吸力侧，在该后缘上可燃燃烧气体。 一对尖叫尖端沿着压力和吸力侧从尖端径向向上延伸，并且在前缘和后缘之间间隔开以限定向上敞开的尖端腔。 至少一个尖叫尖端包括径向向内延伸到尖端盖的槽，槽也沿着尖端和前缘​​之间延伸。 多个间隔开的供应孔径向地延伸穿过狭缝中的尖端帽，与冷却回路流体连通，以将冷却剂引导到槽中以冷却鸣叫器尖端。 然后可以将热障涂层设置在发声器末端的外侧，以提供与可沿其流动的燃烧气体隔离。