公开(公告)号：US08277169B2

公开(公告)日：2012-10-02

申请号：US11155399

申请日：2005-06-16

申请人： Ardeshir Riahi ,  Frederick G. Borns ,  Vivek Agarwal

发明人： Ardeshir Riahi ,  Frederick G. Borns ,  Vivek Agarwal

IPC分类号： F01D5/08

CPC分类号： F01D5/081 ,  Y02T50/676

摘要： Disclosed herein is an apparatus comprising a disk coverplate for a turbine rotor, the disk coverplate comprising a plurality of cooling holes, wherein the distance between the centers of any two adjacent cooling holes is greater than twice the average diameter of the two adjacent cooling holes. A method to control turbine cooling air flow is also disclosed.

摘要翻译： 本文公开了一种包括用于涡轮转子的盘盖板的装置，盘盖板包括多个冷却孔，其中任何两个相邻冷却孔的中心之间的距离大于两个相邻冷却孔的平均直径的两倍。 还公开了一种控制涡轮机冷却空气流动的方法。

公开(公告)号：US6019580A

公开(公告)日：2000-02-01

申请号：US28146

申请日：1998-02-23

申请人： Lawrence D. Barr ,  Frederick G. Borns ,  Mark C. Johnson

发明人： Lawrence D. Barr ,  Frederick G. Borns ,  Mark C. Johnson

IPC分类号： F01D5/30 ,  B63H1/16

CPC分类号： F01D5/3007

摘要： A turbine or compressor disk assembly comprises a plurality of blades attached to a central hub by means of the blade root of each blade engaging a corresponding slot in the hub. According to the principles of the present invention, a turbine or compressor disk assembly includes one or more locally bulging regions extending axially away from the surface of the disk in the vicinity of the bottom contact plane of the disk attachment firtree. The locally bulging regions reduce the peak Macke stress in the disk bottom fillet and blade attachment root. In an illustrative embodiment, two locally bulging regions are incorporated into the disk and the corresponding blades, one of which extends forward from the leading edge of the disk and the other of which extends rearward from the trailing edge of the disk. The rearward locally bulging region has an exaggerated extension which allows the stress reduction ring to form an aft flow discourager as well as functioning to reduce peak stress.

摘要翻译： 涡轮机或压缩机盘组件包括通过每个叶片的叶片根部连接到中心毂的多个叶片，其接合毂中的相应狭槽。 根据本发明的原理，涡轮机或压缩机盘组件包括一个或多个局部凸起区域，其在盘附接件的底部接触平面附近轴向远离盘的表面延伸。 局部凸起区域减小了圆盘底部圆角和刀片附件根部的Macke应力峰值。 在一个说明性实施例中，两个局部凸起区域被结合到盘和相应的叶片中，其中一个叶片从盘的前缘向前延伸，另一个从盘的后缘向后延伸。 后向局部凸起区域具有夸张的延伸部，其允许应力减小环形成后流动鼓风机以及用于减小峰值应力的功能。

公开(公告)号：US06792757B2

公开(公告)日：2004-09-21

申请号：US10288950

申请日：2002-11-05

申请人： Frederick G. Borns ,  Ardeshir Riahi

发明人： Frederick G. Borns ,  Ardeshir Riahi

IPC分类号： F02G100

CPC分类号： F23R3/10 ,  F23R3/50 ,  F23R2900/03044 ,  Y02T50/675

摘要： A heat shield for a combustor dome includes U-shaped baffles on the outer diameter area of the upstream surface of the heat shield. The baffles are clocked with respect to the impingement openings in the combustor dome. The baffles increase cooling of the heat shield by segregating the cooling air flow from the impingement openings and by reducing cross-flow at the outer diameter of the heat shield. The baffles also function as heat shield stiffeners. Slots extend radially inward from the outer rim of the heat shield. Keyholes are at the inner ends of the slots. The slots and keyholes reduce the hoop stresses of the heat shield.

摘要翻译： 用于燃烧器穹顶的隔热罩在隔热罩的上游表面的外径区域上包括U形挡板。 挡板相对于燃烧器穹顶中的冲击开口计时。 挡板通过将冷却空气流从冲击开口偏离并减少隔热罩外径处的横流来增加隔热罩的冷却。 挡板还起到隔热板加强件的作用。 插槽从隔热罩的外缘径向向内延伸。 钥匙孔位于插槽的内端。 槽和钥匙孔减少了隔热罩的环向应力。

公开(公告)号：US07223072B2

公开(公告)日：2007-05-29

申请号：US10766231

申请日：2004-01-27

申请人： Ardeshir Riahi ,  Robert McDonald ,  Frederick G. Borns

发明人： Ardeshir Riahi ,  Robert McDonald ,  Frederick G. Borns

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2250/28 ,  F05D2260/202 ,  Y02T50/67 ,  Y02T50/676 ,  Y10T29/49341 ,  Y10T29/49995

摘要： An airfoil for a gas turbine engine blade includes a plurality of film cooling holes extending through its outer surface. The film cooling holes are formed by defining at least a first datum structure and a second datum structure, and then forming each film cooling hole at a location on the airfoil outer surface relative to the first and second datum structures. As a result, each film cooling hole has a centerline extending therethrough that forms a compound angle with respect to a tangent to the outer surface, and the distance between the centerlines of each film cooling hole is at least a predetermined minimum distance.

摘要翻译： 用于燃气涡轮发动机叶片的翼型件包括延伸穿过其外表面的多个薄膜冷却孔。 通过限定至少第一基准结构和第二基准结构形成薄膜冷却孔，然后在翼型件外表面上相对于第一和第二基准结构的位置处形成每个薄膜冷却孔。 结果，每个薄膜冷却孔具有穿过其延伸的中心线，其相对于外表面的切线形成复合角度，并且每个薄膜冷却孔的中心线之间的距离至少为预定的最小距离。

公开(公告)号：US5106266A

公开(公告)日：1992-04-21

申请号：US577849

申请日：1990-08-30

申请人： Frederick G. Borns ,  Barry S. Bixler

发明人： Frederick G. Borns ,  Barry S. Bixler

IPC分类号： F01D5/28 ,  F01D5/30

CPC分类号： F01D5/30 ,  F01D5/28 ,  F01D5/3007 ,  Y02T50/672

摘要： A single crystal turbine blade has a portion of its attachment section reinforced by a core containing a fine grained, polycrystalline alloy. The blade is prepared by casting a single crystal body with a cavity within the attachment section, and then filling the attachment section with the polycrystalline superalloy to form a composite structure. Filling is preferably accomplished by plasma spraying the cavity with the superalloy, and hot isostatically compacting the sprayed superalloy to minimize porosity. The composite structure is then heat treated to develop an optimized microstructure in the dual alloy attachment section. The resulting turbine blade has improved low cycle fatigue life of the composite attachment section.

摘要翻译： 单晶玻璃叶片的一部分附着部分由含有细晶粒多晶合金的核心增强。 通过在连接部分内铸造具有空腔的单晶体，然后用多晶超合金填充附接部分以形成复合结构来制备刀片。 填充优选通过用超级合金等离子体喷涂空腔来实现，并且热等静压压喷涂的超合金以最小化孔隙率。 然后将复合结构热处理，以在双合金附着部分中形成优化的微结构。 所得到的涡轮叶片具有改善的复合附接部分的低循环疲劳寿命。