公开(公告)号：US07182576B2

公开(公告)日：2007-02-27

申请号：US10881506

申请日：2004-06-29

申请人： Ronald Scott Bunker ,  Ching-Pang Lee

发明人： Ronald Scott Bunker ,  Ching-Pang Lee

IPC分类号： F01D5/18

CPC分类号： 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

摘要： 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.

摘要翻译： 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：US20070022741A1

公开(公告)日：2007-02-01

申请号：US10571850

申请日：2004-09-10

申请人： Anton Frobhlich

发明人： Anton Frobhlich

IPC分类号： F02K9/42

CPC分类号： F02K9/64 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y10T29/49231 ,  Y10T29/4932 ,  Y10T29/49346

摘要： The invention relates to a combustion chamber (1) for a rocket engine, which is used to expel a hot gaseous stream, said combustion chamber (1) having cooling channels (2) that are traversed by a coolant. According to the invention, the cooling channels (2) have a substantially right-angular cross-section and at least some of said channels (2) comprise depressions (6), which prevent the stratification of the coolant in the channels (2). The depressions are formed by the drilling of bores in the combustion chamber wall prior to the production of the cooling channels.

摘要翻译： 本发明涉及一种用于排出热气流的用于火箭发动机的燃烧室（1），所述燃烧室（1）具有由冷却剂穿过的冷却通道（2）。 根据本发明，冷却通道（2）具有基本上为直角的横截面，并且所述通道（2）中的至少一些包括凹陷（6），其防止通道（2）中的冷却剂分层。 凹陷通过在制造冷却通道之前在燃烧室壁中钻孔而形成。

公开(公告)号：US20060285974A1

公开(公告)日：2006-12-21

申请号：US11160272

申请日：2005-06-16

申请人： Ronald Bunker ,  Gary Itzel

发明人： Ronald Bunker ,  Gary Itzel

IPC分类号： F01D5/18

CPC分类号： F01D5/20 ,  F05C2201/0463 ,  F05C2201/0466 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141

摘要： A tip cap piece for use in a turbine bucket. The tip cap piece may include a cold side and a number of pins positioned on the cold side.

摘要翻译： 用于涡轮机桶的顶盖件。 尖端盖可以包括冷侧和位于冷侧的多个销。

公开(公告)号：US20060060334A1

公开(公告)日：2006-03-23

申请号：US10945477

申请日：2004-09-20

申请人： Christopher Joe ,  Paul Lutjen

发明人： Christopher Joe ,  Paul Lutjen

IPC分类号： F28F13/12

CPC分类号： F01D5/187 ,  F01D25/12 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  Y02T50/676

摘要： A compact heat exchanger pedestal array for augmenting heat transfer in a machine is disclosed. The compact heat exchanger pedestal array includes a wall having first and second surfaces. The first surface faces a heated flow path and the second surface partially forms a flow path for cooling fluid. A plurality of pedestals extend from the second surface of the wall. At least one turbulator strip extends between adjacent pedestals. The turbulator strips and pedestals are operable for mixing the cooling fluid to increase heat transfer from the wall to the cooling fluid.

摘要翻译： 公开了一种用于增加机器中的热传递的紧凑型热交换器基座阵列。 紧凑型热交换器基座阵列包括具有第一和第二表面的壁。 第一表面面向加热的流动路径，第二表面部分地形成用于冷却流体的流动路径。 多个基座从壁的第二表面延伸。 至少一个湍流条在相邻基座之间延伸。 紊流器条和基座可操作用于混合冷却流体以增加从壁到冷却流体的热传递。

公开(公告)号：US20050260076A1

公开(公告)日：2005-11-24

申请号：US11131200

申请日：2005-05-18

申请人： Stephan Daux ,  Chantal Giot ,  Hugues Joubert ,  Benjamin Sauthier

发明人： Stephan Daux ,  Chantal Giot ,  Hugues Joubert ,  Benjamin Sauthier

IPC分类号： F01D5/18 ,  F02C7/18 ,  B63H1/14

CPC分类号： F01D5/187 ,  F05D2260/2214

摘要： A blade for a turbomachine gas turbine, the blade having a cooling circuit comprising at least one cooling cavity with a high aspect ratio extending radially between a root and a tip of the blade, and at least one air admission opening at a radially inner end of the cavity to feed it with cooling air, at least one of the walls of the cooling cavity being provided with a plurality of indentations so as to disturb the flow of cooling air in said cavity and increase heat exchange.

摘要翻译： 一种用于涡轮机燃气轮机的叶片，所述叶片具有冷却回路，所述冷却回路包括至少一个冷却空腔，所述至少一个冷却腔具有在所述叶片的根部和所述尖端之间径向延伸的高纵横比，以及至少一个在所述叶片的径向内端的空气入口 所述腔体用冷却空气供给，所述冷却腔的壁中的至少一个设置有多个压痕，以便扰乱所述空腔中的冷却空气的流动并增加热交换。

公开(公告)号：US20050118023A1

公开(公告)日：2005-06-02

申请号：US10881506

申请日：2004-06-29

申请人： Ronald Bunker ,  Ching-Pang Lee

发明人： Ronald Bunker ,  Ching-Pang Lee

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

CPC分类号： 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

摘要： 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.

摘要翻译： 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：US06722134B2

公开(公告)日：2004-04-20

申请号：US10065115

申请日：2002-09-18

申请人： Ronald Scott Bunker

发明人： Ronald Scott Bunker

IPC分类号： F02C718

CPC分类号： F01D5/286 ,  F05D2250/60 ,  F05D2250/712 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2300/501

摘要： A turbine component having a surface provided with a heat transfer enhancement feature formed therein that includes at least one linear surface concavity comprised of plural overlapped surface concavities.

摘要翻译： 一种具有形成有传热增强特征的表面的涡轮机部件，其包括由多个重叠表面凹部组成的至少一个线性表面凹部。

公开(公告)号：US5976337A

公开(公告)日：1999-11-02

申请号：US958360

申请日：1997-10-27

申请人： Paul Stephen Korinko ,  Mark Lawrence Hunt

发明人： Paul Stephen Korinko ,  Mark Lawrence Hunt

IPC分类号： B23K1/00 ,  C25D13/02 ,  C25D13/12 ,  F01D5/18 ,  C25D13/00

CPC分类号： B23K1/0018 ,  C25D13/02 ,  C25D13/12 ,  F01D5/187 ,  B23K2201/001 ,  F05D2260/2212 ,  F05D2260/2214 ,  Y02T50/676

摘要： A method of brazing which includes deposition of brazing material by electrophoresis. Deposition is performed with a low viscosity, low surface tension bath comprising an alcohol, a nitroalkane, and a complex ionic solute. Brazing powder is added to this bath in the quantity of about 0.02 to about 0.04 kilograms per liter. A nonconductive coating is applied to areas where a brazing material should not be deposited, such as small passageways. This method is shown to be useful in applying brazing material adjacent small passageways, such that the brazing material is accurately deposited and does not flow into and interfere with the passageway after the braze joint is formed.

摘要翻译： 一种钎焊方法，包括通过电泳沉积钎料。 用低粘度，低表面张力浴包含醇，硝基烷烃和复合离子溶质进行沉积。 以每公升约0.02至约0.04公斤的量将钎焊粉末加入该浴中。 将非导电涂层施加到不能沉积钎焊材料的区域，例如小通道。 该方法被证明可用于在小通道附近施加钎焊材料，使得钎焊材料在钎焊接头形成之后被精确地沉积并且不流入并干扰通道。

公开(公告)号：US5779447A

公开(公告)日：1998-07-14

申请号：US800985

申请日：1997-02-19

申请人： Yasuoki Tomita ,  Lars Thomsen

发明人： Yasuoki Tomita ,  Lars Thomsen

IPC分类号： F01D5/18 ,  F04D29/58

CPC分类号： F01D5/187 ,  F05D2240/81 ,  F05D2260/2214

摘要： A gas turbine rotor, more particularly a gas turbine rotor blade, which is manufactured so as to be longer, larger, and thin walled and is provided on a rear side of a gas turbine blade array. The gas turbine rotor blade is cooled with cooling air flowing interiorly thereof. A cavity is provided to facilitate the flow of cooling air. The cavity is formed inside a rotor root and inside a hub unit disposed adjacent to a rotor profile unit. Projections are provided inside of the cavity so that the projections, which protrude from an inner wall of the cavity, project into the cooling air flow. Consequently, cooling efficiency of the rotor blade can be improved, and the strength of the portions forming the cavity can be significantly increased. The device also allows the core for cooling to be manufactured and easily set.

摘要翻译： 燃气轮机转子，更具体地，燃气轮机转子叶片，其被制造为更长，更大和薄壁，并且设置在燃气轮机叶片阵列的后侧。 燃气轮机转子叶片由其内部流动的冷却空气冷却。 提供空腔以便于冷却空气的流动。 空腔形成在转子根部内部和靠近转子轮廓单元设置的轮毂单元内部。 突出部设置在腔体的内部，使得从空腔的内壁突出的突出部突出到冷却空气流中。 因此，能够提高转子叶片的冷却效率，能够显着提高形成空腔的部分的强度。 该装置还允许芯体制造和容易设置。

公开(公告)号：US5370499A

公开(公告)日：1994-12-06

申请号：US830144

申请日：1992-02-03

申请人： Ching-Pang Lee

发明人： Ching-Pang Lee

IPC分类号： F01D5/18 ,  B63H1/14

CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2260/202 ,  F05D2260/2214 ,  Y02T50/676

摘要： A turbine airfoil has a mesh cooling hole arrangement which includes first and second pluralities of cooling holes extending between internal and external surfaces of an airfoil side wall at least at a pressure side and extending from an internal chamber to the airfoil exterior. The cooling holes of each plurality extend generally parallel to one another. The cooling holes of the first and second pluralities intersect so as to define a plurality of spaced apart internal solid nodes in the side wall having pairs of opposite sides interconnected by pairs of opposite corners. The spaced nodes define a multiplicity of hole portions of the cooling holes which extend between and along opposite sides of adjacent nodes and a plurality of flow intersections which interconnect the hole portions of the cooling holes and are disposed between the corners of adjacent nodes. The sides of the nodes have lengths which are greater than the widths of the hole portions between adjacent nodes such that, when cooling fluid is passed through the cooling holes, jet flow actions are created through the hole portions which in turn generate jet interactions at the flow intersections to cause restriction of air flow and produce a pressure drop. Also, the cooling holes have flow inlets at the internal surface and flow outlets at the external surface of the airfoil side wall. The area of the flow inlets is substantially less than the area of the flow outlets.

摘要翻译： 涡轮机翼片具有网状冷却孔装置，其包括第一和第二多个冷却孔，其至少在压力侧在翼型侧壁的内表面和外表面之间延伸并且从内室延伸到翼型件外部。 每个多个冷却孔通常彼此平行地延伸。 第一和第二多个的冷却孔相交，以在侧壁中限定多个间隔开的内部实心节点，其具有通过成对的相对角互相连接的成对的相对侧。 间隔开的节点限定了冷却孔的多个孔部分，这些孔部分在相邻节点的相对侧面之间延伸并且沿相邻节点的相对侧延伸，以及多个流动交叉点，其互连冷却孔的孔部分并且设置在相邻节点的角部之间。 节点的侧面具有大于相邻节点之间的孔部分的宽度的长度，使得当冷却流体通过冷却孔时，通过孔部分产生喷射流动作用，这些孔部分又在其中产生射流相互作用 流动交叉点，以引起空气流动的限制并产生压降。 此外，冷却孔在内表面具有流入口，在翼型件侧壁的外表面具有流出口。 流入口的面积大大小于流出口的面积。