公开(公告)号：US06234755B1

公开(公告)日：2001-05-22

申请号：US09411206

申请日：1999-10-04

申请人： Ronald Scott Bunker ,  Jeremy Clyde Bailey ,  Ching-Pang Lee ,  Nesim Abuaf

发明人： Ronald Scott Bunker ,  Jeremy Clyde Bailey ,  Ching-Pang Lee ,  Nesim Abuaf

IPC分类号： F01D518

CPC分类号： F01D5/20 ,  F01D5/186 ,  F01D5/288 ,  F01D25/12 ,  F05D2230/90 ,  F05D2260/202 ,  F05D2260/221 ,  F05D2300/611 ,  Y02T50/67 ,  Y02T50/676

摘要： A method is described for improving the cooling effectiveness of a fluid which flows through a row of passage holes in a substrate (e.g., a turbine component), out to a high-temperature surface of the substrate. The method involves forming a slot over the holes, within the high temperature surface of the substrate. The slot can be formed within protective coatings applied over the substrate. Alternatively, it can be formed partially within the substrate, and partially within the protective coatings. Movement of a film coolant through the substrate and into the slot results in greater cooling effectiveness. Related articles are also described.

摘要翻译： 描述了一种用于改善流过基板（例如，涡轮机部件）中的一排通道孔的流体到基板的高温表面的冷却效率的方法。 该方法包括在衬底的高温表面内在孔上形成槽。 槽可以形成在施加在基板上的保护涂层内。 或者，其可以部分地形成在基底内，部分地形成在保护性涂层内。 薄膜冷却剂通过基底并进入槽中的运动导致更大的冷却效果。 还描述了相关文章。

公开(公告)号：US5651662A

公开(公告)日：1997-07-29

申请号：US968544

申请日：1992-10-29

申请人： Ching-Pang Lee ,  Ronald Scott Bunker ,  Nesim Abuaf

发明人： Ching-Pang Lee ,  Ronald Scott Bunker ,  Nesim Abuaf

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2250/12 ,  F05D2250/121 ,  F05D2260/202

摘要： A wall adapted for use in a gas turbine engine between a first and a hotter second fluid includes a first side over which is flowable the first fluid, and an opposite second side over which is flowable the second fluid. An elongate slot extends inwardly from the second side and is disposed in flow communication with a plurality of longitudinally spaced apart holes extending inwardly from the first side. The holes are disposed at a compound angle relative to the second side for discharging the first fluid obliquely into the slot and at a shallow discharge angle from the slot along the second side. In a preferred embodiment, the slot has an aft surface including a plurality of longitudinally spaced apart grooves extending from the holes to the wall second side.

摘要翻译： 适于在第一和第二热液体之间的燃气涡轮发动机中使用的壁包括可流过第一流体的第一侧和可流动第二流体的相对的第二侧。 细长狭槽从第二侧向内延伸，并且设置成与从第一侧向内延伸的多个纵向间隔开的孔流动连通。 孔以相对于第二侧的复合角度设置，用于将第一流体倾斜地排放到槽中，并且沿着沿着第二侧的槽沿浅放电角排放。 在优选实施例中，槽具有包括从孔延伸到壁第二侧的多个纵向间隔开的槽的后表面。

公开(公告)号：US5337568A

公开(公告)日：1994-08-16

申请号：US43167

申请日：1993-04-05

申请人： Ching-Pang Lee ,  Steven G. Goebel ,  Nesim Abuaf

发明人： Ching-Pang Lee ,  Steven G. Goebel ,  Nesim Abuaf

IPC分类号： F01D5/18 ,  F23R3/00 ,  F23R3/16

CPC分类号： F01D5/18 ,  F23R3/002 ,  F05D2250/181 ,  F05D2250/182 ,  F05D2250/183 ,  F05D2250/294 ,  F05D2260/221 ,  F05D2260/2212 ,  Y02T50/676

摘要： A gas turbine engine hot section component such as a turbine blade or vane having an airfoil is provided a non-film cooled portion of a heat transfer wall having a hot surface and a plurality of longitudinally extending micro-grooves disposed in the portion of the wall along the hot surface in a direction parallel to the direction of the hot gas flow. The depth of the micro-grooves is very small and on the order of magnitude of a predetermined laminar sublayer of a turbulent boundary layer. The grooves are sized so as to alter the boundary layer thickness near the leading edge of the airfoil to reduce heat transfer from the hot gas flow to the airfoil near the leading edge. In one embodiment the micro-grooves are about 0.001 inches deep and have a preferred depth range of from about 0.001 inches to 0.005 inches and which are square, rectangular, or triangular in cross-section and the micro-grooves are spaced about one width apart.

摘要翻译： 具有翼型的涡轮机叶片或叶片的燃气涡轮发动机热段部件设置有具有热表面的传热壁的非薄膜冷却部分和设置在壁的部分中的多个纵向延伸的微槽 沿着热表面平行于热气流的方向。 微槽的深度非常小，并且在湍流边界层的预定层状亚层的数量级上。 这些槽的尺寸被设计成改变靠近翼型的前缘附近的边界层厚度，以减少从热气流到靠近前缘的翼型件的热传递。 在一个实施例中，微槽约为0.001英寸深，并且具有约0.001英寸至0.005英寸的优选深度范围，并且其横截面为正方形，矩形或三角形，并且微槽间隔约一分之一宽度 。

公开(公告)号：US5980209A

公开(公告)日：1999-11-09

申请号：US884091

申请日：1997-06-27

申请人： Vincent Anthony Barry ,  Brent A. Gregory ,  Nesim Abuaf

发明人： Vincent Anthony Barry ,  Brent A. Gregory ,  Nesim Abuaf

IPC分类号： F01D5/14 ,  F01D5/18 ,  F01D5/30

CPC分类号： F01D5/141 ,  F01D5/187 ,  Y10S416/05

摘要： A first-stage turbine blade includes an airfoil having a profile according to Table I. The airfoil has a plurality of cooling air passages extending linearly from the root portion to the tip portion of the airfoil. The blade includes a shank having a pair of cavities in communication through the blade dovetail with a plenum in the wheel space for supplying cooling air to the passages in the airfoil. The cooling passages in the airfoil terminate in a recess at the tip portion which has an opening adjacent the trailing edge of the airfoil and along the suction side to enable egress of cooling air into the hot gas stream on the low pressure side of the airfoil. The majority of the cooling passages are turbulated. Certain of those passages are arranged in rows lying adjacent to the pressure and suction sides of the airfoil.

摘要翻译： 第一级涡轮机叶片包括具有根据表I的轮廓的翼型件。翼型件具有多个冷却空气通道，该冷却空气通道从翼部的根部直线延伸到翼型部分。 叶片包括具有一对空腔的柄，所述一对空腔通过叶片燕尾榫与在车轮空间中的增压室连通，用于向翼型中的通道供应冷却空气。 翼型件中的冷却通道终止在尖端部分处的凹部中，该凹部具有与翼型件的后缘相邻并且沿着吸力侧的开口，以使冷却空气能够排出到翼型的低压侧上的热气流中。 大部分冷却通道是混浊的。 这些通道中的某些通道排列成与翼型的压力和吸力侧相邻的排。

公开(公告)号：US5822853A

公开(公告)日：1998-10-20

申请号：US669069

申请日：1996-06-24

申请人： Ann Melinda Ritter ,  John Raymond Hughes ,  Melvin Robert Jackson ,  Francis Lawrence Kirkpatrick ,  Francisco Jose Tenreiro Cunha ,  Nesim Abuaf ,  Ronald Scott Bunker

发明人： Ann Melinda Ritter ,  John Raymond Hughes ,  Melvin Robert Jackson ,  Francis Lawrence Kirkpatrick ,  Francisco Jose Tenreiro Cunha ,  Nesim Abuaf ,  Ronald Scott Bunker

IPC分类号： F02C7/00 ,  B22F5/10 ,  B23K20/00 ,  B23P15/00 ,  F23R3/00 ,  F23R3/42

CPC分类号： F23R3/005 ,  B22F5/10 ,  B23P15/00 ,  B22F2005/103 ,  B23P2700/13 ,  F05B2250/231 ,  Y02T50/675 ,  Y10T29/49346 ,  Y10T29/49353

摘要： Methods of making cylindrical structures with cooling channels, such as, for example, combustor/transition pieces for gas turbines having a double wall with a plurality of cooling channels, both axially and, in some cases, circumferential cross-flow passages positioned between the structure's inner member and the outer member to provide cooling air thereto, are disclosed. The cooling channels are formed in the area between the inner member of the structure and the outer member thereof. The passages preferably extend both axially and circumferentially with respect to the direction of flow through the structure. The axial passages extend completely from one end to the other and the circumferential passages extend around the circumference of the structure.

摘要翻译： 制造具有冷却通道的圆柱形结构的方法，例如用于燃气轮机的燃烧器/过渡件，其具有带有多个冷却通道的双壁，轴向和在一些情况下位于结构的 内部构件和外部构件以提供冷却空气。 冷却通道形成在结构的内部构件和其外部构件之间的区域中。 通道优选地相对于通过结构的流动方向轴向地和周向地延伸。 轴向通道从一端到另一端完全延伸，周向通道围绕结构的圆周延伸。

公开(公告)号：US4798753A

公开(公告)日：1989-01-17

申请号：US157156

申请日：1988-02-11

申请人： Nesim Abuaf ,  Robert W. Barito ,  Kenneth L. Downs

发明人： Nesim Abuaf ,  Robert W. Barito ,  Kenneth L. Downs

IPC分类号： C04B30/00 ,  E04B1/80 ,  F25D23/06 ,  B32B1/02 ,  B32B9/00

CPC分类号： F25D23/06 ,  C04B30/00 ,  E04B1/806 ,  F25D2201/122 ,  Y02W30/92 ,  Y10T428/231 ,  Y10T428/239

摘要： Insulating panels are formed from compressed particulate material impregnated with insulating gases, the combination being held in a gas tight pouch. These pouches can be placed in the insulation space of a structure where insulation is to be provided and, if desired, encapsulated in a foamed insulating material. Among the possible particulate materials is precipitated silica, while various Freon gases can be employed as the insulating gas.

摘要翻译： 绝缘板由浸渍有绝缘气体的压缩颗粒材料形成，该组合被保持在气密袋中。 这些袋可以放置在要提供绝缘的结构的绝缘空间中，并且如果需要，封装在泡沫绝缘材料中。 可能的颗粒材料中有沉淀二氧化硅，而可以使用各种氟利昂气体作为绝缘气体。

公开(公告)号：US06183197B2

公开(公告)日：2001-02-06

申请号：US09253367

申请日：1999-02-22

申请人： Ronald Scott Bunker ,  Nesim Abuaf

发明人： Ronald Scott Bunker ,  Nesim Abuaf

IPC分类号： F01D508

CPC分类号： F01D5/141 ,  F05D2260/231 ,  Y02T50/67 ,  Y02T50/673 ,  Y02T50/675 ,  Y10S415/914

摘要： An airfoil with a reduced heat load for use in either a turbine or a compressor of a gas turbine engine comprises having at least one heat reducing dimple on the body of the airfoil or on the associated endwall of the airfoil. The body of the airfoil is comprised of a leading edge, a trailing edge, a pressure side and a suction side. The length of the heat reducing dimple in the expected direction of hot gas stream flow is at least equal to or greater than the width transverse to such direction. The heat reducing dimple is located on the airfoil or endwall so as to reduce the heat load as the hot gas stream flow passes from the leading edge to the trailing edge.

摘要翻译： 具有用于燃气涡轮发动机的涡轮或压缩机中的具有降低的热负荷的翼型件包括在翼型体的主体或翼型的相关端壁上具有至少一个减热凹坑。 机翼的主体由前缘，后缘，压力侧和吸力侧构成。 热气流期望方向上的减热凹坑的长度至少等于或大于横向于该方向的宽度。 减热凹坑位于翼型件或端壁上，以便随着热气流从前缘到后缘流动而减少热负荷。

公开(公告)号：US5749229A

公开(公告)日：1998-05-12

申请号：US542982

申请日：1995-10-13

申请人： Nesim Abuaf ,  Steven George Goebel

发明人： Nesim Abuaf ,  Steven George Goebel

IPC分类号： F02K1/82 ,  F23R3/00 ,  F02C1/00

CPC分类号： F23R3/002 ,  F02K1/82 ,  F05D2260/201 ,  F23R2900/03044 ,  Y02T50/67 ,  Y02T50/675 ,  Y10S60/909 ,  Y10T428/12611

摘要： A combustor liner includes an inner layer for facing combustion gases, and an opposite outer layer for facing a cooling fluid. The outer layer has a greater coefficient of thermal conductivity than the inner layer for reducing temperature gradients in the liner. In a preferred embodiment, the outer layer significantly reduces temperature gradients in the liner which are caused by the varying cooling ability of impingement cooling air jets for more uniformly cooling the combustor liner and reducing the maximum temperature thereof.

摘要翻译： 燃烧器衬套包括用于面对燃烧气体的内层和用于面对冷却流体的相对的外层。 外层具有比内层更大的导热系数，用于降低内衬中的温度梯度。 在一个优选实施例中，外层显着降低了衬套中的温度梯度，这是由冲击冷却空气射流变化的冷却能力引起的，用于更均匀地冷却燃烧器衬套并降低其最大温度。

公开(公告)号：US5413463A

公开(公告)日：1995-05-09

申请号：US814607

申请日：1991-12-30

申请人： Paul Chiu ,  Nesim Abuaf

发明人： Paul Chiu ,  Nesim Abuaf

IPC分类号： F01D5/18 ,  F02C7/18 ,  F01D5/08

CPC分类号： F01D5/187 ,  F05D2230/11 ,  F05D2260/2212

摘要： A turbine blade includes a plurality of cooling passages each having a turbulated section of the passage preferentially located along the portion of the turbine blade subjected to the highest temperature. Thus, turbulent air flow is provided in intermediate sections of the blade to enhance the heat exchange relation with the metal of the blade. The bores of the cooling passages adjacent the tip and root portions are smooth and provide adequate cooling in those sections at a lower heat exchange relationship. The cooling passage bores are formed by an electrochemical machining process using an elongated electrode with a chemical electrolyte for forming enlarged cavities within the blade.

摘要翻译： 涡轮机叶片包括多个冷却通道，每个冷却通道具有通道的湍流部分，优先沿着经受最高温度的涡轮机叶片的部分定位。 因此，在叶片的中间部分设置湍流气流，以增强与叶片的金属的热交换关系。 靠近尖端和根部的冷却通道的孔是平滑的，并且在那些部分中以较低的热交换关系提供足够的冷却。 冷却通道孔通过使用具有化学电解质的细长电极的电化学机械加工工艺形成，所述细长电极用于在刀片内形成扩大的空腔。

公开(公告)号：US5960632A

公开(公告)日：1999-10-05

申请号：US912529

申请日：1997-08-18

申请人： Nesim Abuaf ,  Steven George Goebel

发明人： Nesim Abuaf ,  Steven George Goebel

IPC分类号： F02K1/82 ,  F23R3/00 ,  F02C1/00

CPC分类号： F23R3/002 ,  F02K1/82 ,  F05D2260/201 ,  F23R2900/03044 ,  Y02T50/67 ,  Y02T50/675 ,  Y10S60/909 ,  Y10T428/12611

摘要： A combustor liner includes an inner layer for facing combustion gases, and an opposite outer layer for facing a cooling fluid. The outer layer has a greater coefficient of thermal conductivity than the inner layer for reducing temperature gradients in the liner. In a preferred embodiment, the outer layer significantly reduces temperature gradients in the liner which are caused by the varying cooling ability of impingement cooling air jets for more uniformly cooling the combustor liner and reducing the maximum temperature thereof.

摘要翻译： 燃烧器衬套包括用于面对燃烧气体的内层和用于面对冷却流体的相对的外层。 外层具有比内层更大的导热系数，用于降低内衬中的温度梯度。 在一个优选实施例中，外层显着降低了衬套中的温度梯度，这是由冲击冷却空气射流变化的冷却能力引起的，用于更均匀地冷却燃烧器衬套并降低其最大温度。