公开(公告)号：US20050111964A1

公开(公告)日：2005-05-26

申请号：US10718149

申请日：2003-11-20

Applicant: Erich Krammer ,  Richard Haubert ,  Ching-Pang Lee ,  Harvey Maclin

Inventor： Erich Krammer ,  Richard Haubert ,  Ching-Pang Lee ,  Harvey Maclin

IPC: F01D5/08 ,  F01D9/02 ,  F01D11/02 ,  F01D25/12 ,  F02C3/067 ,  F02C6/08 ,  F02C7/12 ,  F02C7/18 ,  F02C7/28 ,  F02C9/22 ,  F16J15/447 ,  F01D5/14

CPC classification number: F01D25/12 ,  F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F02C7/18 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbofan engine includes in serial flow communication a first fan, second fan, multistage compressor, combustor, first turbine, second turbine, and third turbine. The first turbine is joined to the compressor by a first shaft. The second turbine is joined to the second fan by a second shaft. And, the third turbine is joined to the first fan by a third shaft. First, second, and third cooling circuits are joined to different stages of the compressor for cooling the forward and aft sides and center bore of the first turbine with different pressure air.

Abstract translation: 涡轮风扇发动机包括串联流动连通的第一风扇，第二风扇，多级压缩机，燃烧器，第一涡轮机，第二涡轮机和第三涡轮机。 第一涡轮机通过第一轴连接到压缩机。 第二涡轮机通过第二轴连接到第二风扇。 并且，第三涡轮机通过第三轴接合到第一风扇。 第一，第二和第三冷却回路连接到压缩机的不同阶段，用不同的压力空气冷却第一涡轮机的前后侧和中心孔。

公开(公告)号：US20050106316A1

公开(公告)日：2005-05-19

申请号：US10714213

申请日：2003-11-13

Applicant: Joseph Rigney ,  Ching-Pang Lee ,  Ramgopal Darolia

Inventor： Joseph Rigney ,  Ching-Pang Lee ,  Ramgopal Darolia

IPC: B23P6/00 ,  C23C26/00 ,  C23C28/00 ,  F01D5/00 ,  F01D5/14 ,  F01D5/28 ,  F01D25/00 ,  F02C7/00 ,  B32B35/00

CPC classification number: C23C28/321 ,  C23C26/00 ,  C23C28/325 ,  C23C28/3455 ,  F01D5/005 ,  F01D5/288 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/501 ,  Y10T29/49318

Abstract: According to an embodiment of the invention, a method for repairing a coated high pressure turbine blade, which has been exposed to engine operation, to restore coated airfoil contour dimensions of the blade, is disclosed. The method comprises providing an engine run high pressure turbine blade including a base metal substrate made of a nickel-based alloy and having thereon a thermal barrier coating system. The thermal barrier coating system comprises a diffusion bond coat on the base metal substrate and a top ceramic thermal barrier coating comprising a yttria stabilized zirconia material. The top ceramic thermal barrier coating has a nominal thickness t. The method further comprises removing the thermal barrier coating system, wherein a portion of the base metal substrate also is removed, and determining the thickness of the base metal substrate removed. The portion of the base metal substrate removed has a thickness, Δt. The method also comprises reapplying the diffusion bond coat to the substrate, wherein the bond coat is reapplied to a thickness, which is about the same as applied prior to the engine operation; and reapplying the top ceramic thermal barrier coating to a nominal thickness of t+Δt, wherein Δt compensates for the portion of removed base metal substrate. Advantageously, the coated airfoil contour dimensions of the high pressure turbine blade are restored to about the coated dimensions preceding the engine run.

Abstract translation: 根据本发明的实施例，公开了一种已经暴露于发动机操作的用于修复涂覆的高压涡轮机叶片以恢复叶片的被覆翼型轮廓尺寸的方法。 该方法包括提供一种发动机运行的高压涡轮叶片，其包括由镍基合金制成的基底金属基底并且具有热障涂层系统。 热障涂层系统包括在基底金属基底上的扩散粘合涂层和包含氧化钇稳定的氧化锆材料的顶部陶瓷热障涂层。 顶部陶瓷热障涂层具有标称厚度t。 该方法还包括去除热障涂层系统，其中基底金属衬底的一部分也被去除，并且确定移除的母体金属衬底的厚度。 去除的贱金属基材的部分厚度为Deltat。 该方法还包括将扩散粘合涂层重新施加到基底上，其中粘结涂层重新施加到与发动机操作前相同的厚度; 并将顶部陶瓷热障涂层重新施加到标称厚度t + Deltat，其中Deltat补偿去除的基底金属基底的部分。 有利地，高压涡轮机叶片的被覆翼型轮廓尺寸恢复到发动机运行之前的涂层尺寸。

公开(公告)号：US20050106021A1

公开(公告)日：2005-05-19

申请号：US10720045

申请日：2003-11-19

Applicant: Ronald Bunker ,  Jeremy Bailey ,  Ching-Pang Lee

Inventor： Ronald Bunker ,  Jeremy Bailey ,  Ching-Pang Lee

IPC: F01D9/02 ,  F01D5/18 ,  F02C7/18 ,  F28F3/02 ,  F28F3/04 ,  F28F13/12 ,  B63H1/14

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 of the wall. The pins define a mesh cooling arrangement having a number of flow channels. A number of dimples are located in at least one of the inner and outer portions of the wall. The component may also include a number of turbulators disposed on at least one of the inner and outer portions 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。 多个销在壁的内部和外部之间延伸。 销钉限定具有多个流动通道的网状冷却装置。 多个凹坑位于壁的内部和外部的至少一个中。 该部件还可以包括设置在壁的内部和外部部分中的至少一个上的多个紊流器。

公开(公告)号：US06617003B1

公开(公告)日：2003-09-09

申请号：US09707023

申请日：2000-11-06

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

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

IPC: B32B1504

CPC classification number: C23C28/3215 ,  C23C28/321 ,  C23C28/325 ,  C23C28/3455 ,  F01D5/182 ,  F01D5/187 ,  F01D5/288 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T428/12611 ,  Y10T428/12736 ,  Y10T428/12944 ,  Y10T428/24273 ,  Y10T428/24289 ,  Y10T428/24298 ,  Y10T428/24306

Abstract: An actively cooled TBC bond coat wherein active convection cooling is provided through micro channels inside or adjacent to a bond coat layer applied to a substrate. The micro channels communicate directly with at least one cooling fluid supply contained within a turbine engine component, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate is covered with an actively cooled bond coat layer, it will reduce the cooling requirement for the substrate, thus allowing the engine to run at higher operating temperature without the need for additional cooling air, achieving a better engine performance. In one form, the component includes a substrate having at least one substrate channel with a first and second end. At least one micro channel is in fluid communication with a plenum which in turn is in fluid communication with at least one substrate channel through an exit orifice in the substrate channel which is at a first end of the substrate channel. A second end of the substrate channel is in communication with a cooling fluid supply, for example, cooling circuits contained within the turbine engine component. The micro channel is located between the substrate surface and the outer gas flow path surface of the component.

Abstract translation: 主动冷却的TBC粘合涂层，其中主动对流冷却通过施加到基底的粘合涂层的内部或附近的微通道提供。 微通道与包含在涡轮发动机部件内的至少一个冷却流体供应件直接连通，从而为粘合涂层提供直接和有效的冷却。 由于衬底被主动冷却的粘合涂层覆盖，所以它将降低衬底的冷却要求，从而允许发动机在更高的工作温度下运行，而不需要额外的冷却空气，实现更好的发动机性能。 在一种形式中，组件包括具有至少一个具有第一和第二端的衬底通道的衬底。 至少一个微通道与气室流体连通，该气室又与通过基板通道中位于衬底通道的第一端处的出口孔与至少一个衬底通道流体连通。 衬底通道的第二端与冷却流体供应源连通，例如包含在涡轮发动机部件内的冷却回路。 微通道位于基板表面和部件的外部气体流动通道表面之间。

公开(公告)号：US06589600B1

公开(公告)日：2003-07-08

申请号：US09345541

申请日：1999-06-30

Applicant: Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson ,  Ching-Pang Lee

Inventor： Wayne Charles Hasz ,  Nesim Abuaf ,  Robert Alan Johnson ,  Ching-Pang Lee

IPC: B05D312

CPC classification number: F28F21/089 ,  B22C9/10 ,  B22C9/22 ,  B22D25/02 ,  F01D5/18 ,  F01D25/08 ,  F05D2260/2214 ,  F23R2900/03045 ,  F28F13/185 ,  F28F21/087

Abstract: A turbine engine component is provided that has a surface that contains a plurality of depressions that are effective to increase the surface area of the component. The depressions are generally concave in contour and improve the heat transfer characteristics of the component. Methods for forming the turbine engine components are also disclosed.

Abstract translation: 提供一种涡轮发动机部件，其具有包含有效增加部件的表面积的多个凹部的表面。 凹陷通常在轮廓上是凹的并且改善了部件的传热特性。 还公开了用于形成涡轮发动机部件的方法。

公开(公告)号：US06582584B2

公开(公告)日：2003-06-24

申请号：US09925024

申请日：2001-08-09

Applicant: Ching-Pang Lee ,  Rong-Shi Paul Chiu

Inventor： Ching-Pang Lee ,  Rong-Shi Paul Chiu

IPC: B23H300

CPC classification number: F28F13/12 ,  B23H9/00 ,  B23H9/006 ,  B23H9/10 ,  B23H9/14 ,  F01D5/187 ,  F05D2260/2212 ,  F28D2021/0078 ,  F28F1/40

Abstract: A method of enhancing heat transfer and cooling efficiency in a cooling passage includes forming a plurality of turbulator rings in the passage, the rings projecting inwardly, substantially perpendicular to a cooling flow direction in the passage; and using a patterned electrode, forming at least one gap in one or more of the turbulator rings, extending substantially parallel to the flow direction.

公开(公告)号：US06546730B2

公开(公告)日：2003-04-15

申请号：US10166748

申请日：2002-06-12

Applicant: Robert Alan Johnson ,  Anthony Joseph Loprinzo ,  Ching-Pang Lee ,  Nesim Abuaf ,  Wayne Charles Hasz ,  Harmon Lindsay Morton

Inventor： Robert Alan Johnson ,  Anthony Joseph Loprinzo ,  Ching-Pang Lee ,  Nesim Abuaf ,  Wayne Charles Hasz ,  Harmon Lindsay Morton

IPC: F02C300

CPC classification number: F23R3/002 ,  F23D2214/00 ,  F23R2900/03045 ,  Y10T29/4932 ,  Y10T29/49348

Abstract: A combustor liner is provided on its backside cooling surface with a braze alloy coating and cooling enhancement material, preferably metallic particles to enhance the heat transfer between the liner and the cooling medium. The surface area of the backside coated area is increased substantially by the coating and particles in relation to the uncoated surface areas. Consequently, the life of the liner is extended.

公开(公告)号：US06528118B2

公开(公告)日：2003-03-04

申请号：US09777930

申请日：2001-02-06

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

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

IPC: C23C1404

CPC classification number: C23C14/042 ,  C23C4/01 ,  C23C28/00 ,  Y02T50/67

Abstract: A process for creating microgrooves within or adjacent to a TBC layer applied to a gas turbine engine component such as a blade or vane. The process includes the steps of applying a bond coat to the surface of the substrate. A wire mesh is placed a predetermined distance above the bond coat surface. With the wire mesh in position, about 0.002 inches of an inner TBC is applied over the bond coat. The wire in the wire mesh causes a shadow effect as the TBC is applied, so that there are variations in the thickness of the applied TBC, forming micro channels. The wire mesh is removed and an additional outer TBC layer is applied over the inner TBC layer, and the variations in thickness are bridged by the continued deposition of the columnar TBC over the inner TBC layer, forming the microgrooves.

公开(公告)号：US06505673B1

公开(公告)日：2003-01-14

申请号：US09473295

申请日：1999-12-28

Applicant: Nesim Abuaf ,  Wayne Charles Hasz ,  Ching-Pang Lee ,  Robert Alan Johnson ,  Frederick Alan Buck

Inventor： Nesim Abuaf ,  Wayne Charles Hasz ,  Ching-Pang Lee ,  Robert Alan Johnson ,  Frederick Alan Buck

IPC: B22C702

CPC classification number: B22C9/10 ,  B22C7/06 ,  B22C23/00 ,  B23K35/3033

Abstract: A method of forming a turbine engine component, includes providing a mold having a textured region, pouring a molten alloy into the mold, and cooling the molten alloy to form a turbine engine component, wherein the turbine engine component has an enhanced surface area region corresponding to the textured region of the mold, the enhanced surface area region comprising randomly arranged bumps.

Abstract translation: 一种形成涡轮发动机部件的方法，包括提供具有纹理区域的模具，将熔融合金浇注到模具中，以及冷却熔融合金以形成涡轮发动机部件，其中涡轮发动机部件具有相应的增强的表面积区域 到模具的纹理区域，增强的表面积区域包括随机排列的凸块。

公开(公告)号：US06499949B2

公开(公告)日：2002-12-31

申请号：US09818385

申请日：2001-03-27

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

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

IPC: F01D518

CPC classification number: F01D5/187 ,  F05D2230/14 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/676 ,  Y10T29/4932

Abstract: The present invention provides active convection cooling through micro channels within or adjacent to a bond coat layer applied to the trailing edge of a turbine engine high pressure airfoil. When placed adjacent to or within a porous TBC, the micro channels additionally provide transpiration cooling through the porous TBC. The micro channels communicate directly with at least one cooling circuit contained within the airfoil from which they receive cooling air, thereby providing direct and efficient cooling for the bond coat layer. Because the substrate includes an actively cooled flow path surface region that can reduce the cooling requirement for the substrate, the engine can run at a higher firing temperature without the need for additional cooling air, achieving a better, more efficient engine performance. In one embodiment, a metallic bond coat is added to an airfoil with pressure side bleed film cooling slots. The bond coat is grooved such that the grooves are structured, with at least one structured micro groove communicating with at least one cooling fluid supply contained within the airfoil. A TBC layer is applied, using a shadowing technique, over the structured grooves, resulting in the formation of hollow micro channels for the transport of the cooling fluid. In different embodiments, the location of the structured grooves, hence, the resulting micro channels are placed within the airfoil substrate at the substrate/bond coat interface or within the TBC layer.

Abstract translation: 本发明提供了在施加到涡轮发动机高压翼型件的后缘上的粘合涂层之内或附近的微通道的主动对流冷却。 当放置在多孔TBC附近或内部时，微通道另外通过多孔TBC提供蒸腾冷却。 微通道与包含在翼片内的至少一个冷却回路直接连通，从而从它们接收冷却空气，从而为粘结涂层提供直接和有效的冷却。 因为基板包括可以降低基板的冷却要求的主动冷却的流动路径表面区域，所以发动机可以在更高的点火温度下运行，而不需要额外的冷却空气，实现更好，更有效的发动机性能。 在一个实施例中，将金属粘合涂层加入到具有压力侧泄放膜冷却槽的翼型件上。 接合涂层是开槽的，使得凹槽被构造成具有与包含在翼型内的至少一个冷却流体供应源连通的至少一个结构化微槽。 使用阴影技术在结构化凹槽上施加TBC层，导致形成用于输送冷却流体的中空微通道。 在不同的实施例中，结构化凹槽的位置，因此，所得到的微通道在衬底/粘结涂层界面处或在TBC层内被放置在翼型衬底内。