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1. 发明授权

US07135863B2 Thermal management system and method for MRI gradient coil 失效
公开(公告)号：US07135863B2
公开(公告)日：2006-11-14
申请号：US10955635
申请日：2004-09-30
申请人： Mehmet Arik , Bulent Aksel , William Dwight Gerstler , Cherik Bulkes , Douglas Arthur Kelley , Steven Joseph Brzozowski
发明人： Mehmet Arik , Bulent Aksel , William Dwight Gerstler , Cherik Bulkes , Douglas Arthur Kelley , Steven Joseph Brzozowski
IPC分类号： G01V3/00
CPC分类号： G01R33/3856
摘要： A thermal management system and method for cooling Magnetic Resonance Imaging gradient coils. The system includes least one first header tube positioned adjacent to said gradient coils and configured to transport a coolant fluid; at least one set of cooling tubes connected to said header tube at inlet ends and configured to transport said coolant fluid, wherein said cooling tubes are parallel to each other and at least one second header tube positioned adjacent to said gradient coils, connected to said at least one set of cooling tubes at outlet ends of said at least one set of cooling tubes and configured to transport said coolant fluid.

2. 发明授权

US5975850A Turbulated cooling passages for turbine blades 失效
标题翻译：用于涡轮叶片的涡轮冷却通道
公开(公告)号：US5975850A
公开(公告)日：1999-11-02
申请号：US772635
申请日：1996-12-23
申请人： Nesim NMN Abuaf , Steven Joseph Brzozowski
发明人： Nesim NMN Abuaf , Steven Joseph Brzozowski
IPC分类号： F01D5/18 , B63H1/14
CPC分类号： F01D5/187 , F05D2260/2214 , Y02T50/676
摘要： A turbine blade including an airfoil section having contoured surface geometries between the consecutive ribs or turbulators on the leading edge passage walls is described. The contoured surface geometries increase the overall heat transfer surface area between adjacent ribs as compared to the heat transfer surface area of a smooth inter-rib wall. The contoured surface geometries do not, however, change the overall serpentine passage geometry or the large scale flow characteristics of the turbulated cooling passageways. The contoured surface geometries may have many different geometries (e.g., triangular, conical, semi-cylindrical, cylindrical columns or indentations in the side wall such as semi-circular dimples).
摘要翻译：描述了包括在前缘通道壁上的连续肋或紊流器之间具有轮廓表面几何形状的翼型部分的涡轮叶片。相对于平滑的肋间壁的传热表面积，轮廓表面几何形状增加了相邻肋之间的总体传热表面积。然而，轮廓的表面几何形状不会改变整个蛇形通道几何形状或紊流冷却通道的大规模流动特性。轮廓表面几何形状可以具有许多不同的几何形状（例如，侧壁中的三角形，圆锥形，半圆柱形，圆柱形或凹陷，例如半圆形凹坑）。

3. 发明授权

US5660525A Film cooled slotted wall 失效
标题翻译：薄膜冷却开槽墙
公开(公告)号：US5660525A
公开(公告)日：1997-08-26
申请号：US94998
申请日：1993-07-23
申请人： Ching-Pang Lee , Ronald Scott Bunker , Nesim Abuaf , Steven Joseph Brzozowski
发明人： Ching-Pang Lee , Ronald Scott Bunker , Nesim Abuaf , Steven Joseph Brzozowski
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. The holes are also disposed in converging pairs to impinge together in the slot the first fluid channeled therethrough. 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。这些孔也以会聚对设置，以将槽中的第一流体冲入其中。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。

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