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1. 发明专利

AU2003204541B2 Improved film cooling for microcircuits 未知
公开(公告)号：AU2003204541B2
公开(公告)日：2005-07-07
申请号：AU2003204541
申请日：2003-06-05
申请人： UNITED TECHNOLOGIES CORP
发明人： ALAHYARI ABBAS A , BLAIR MICHAEL F , DRAPER SAMUEL DAVID
IPC分类号： B81B1/00 , B81B7/04 , F01D5/18 , F01D9/02 , F01D25/12 , F01D25/24 , F02C7/18 , F02C7/28 , F23M5/08 , F23R3/00 , F23R3/06 , F25D9/00 , F28F13/02 , F02C007/18 , F01P001/00 , F01D025/12 , F02C007/12
摘要： An embedded microcircuit (5) for producing an improved cooling film over a surface of a part, comprises an inlet through which a coolant gas may enter, a circuit channel (29) extending from the inlet through which the coolant gas may flow, and a slot film hole (31) formed at a terminus of the circuit channel (29) through which the coolant gas may exit a part.

2. 发明专利

AU2003204539B2 Linked, manufacturable, non-plugging microcircuits 未知
公开(公告)号：AU2003204539B2
公开(公告)日：2004-12-16
申请号：AU2003204539
申请日：2003-06-05
申请人： UNITED TECHNOLOGIES CORP
发明人： DRAPER SAMUEL DAVID
IPC分类号： F01D5/18 , F01D9/02 , F01D25/12 , F02C7/18 , F23M5/08 , F23R3/00 , F25D9/00 , F28D7/08 , F02C007/18 , F01P001/00 , F01D025/12 , F02C007/12
摘要： A linked microcircuit (7) for providing coolant gas flow through an aircraft part, comprises at least one inlet through which a coolant gas may enter, a circuit channel (29) extending from the at least one inlet through which the coolant gas may flow. The circuit channel (29) is formed from the superimposition of a plurality of alternating serpentine circuits. At least one outlet (30) is appended to the circuit channel 29 through which the coolant gas may exit the circuit channel.

3. 发明申请

US20030161718A1 Thermally isolated housing in gas turbine engine 失效
公开(公告)号：US20030161718A1
公开(公告)日：2003-08-28
申请号：US10084209
申请日：2002-02-25
申请人： Honeywell International, Inc.
发明人： Ly D. Nguyen , Louis Cruse , Ivar Gene Fowkes , Silvestre Salas , William North , Vadanth Kadambi
IPC分类号： F01D025/12
CPC分类号： F01D9/065 , F01D25/14
摘要： An apparatus and system for thermally isolating a gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is assembled within the housing with an outer baffle surrounding the floating liner and an inner baffle disposed within the floating liner. The floating liner creates a thermally isolated device to cover and protect the housing from high temperature. Openings formed in the outer baffle, floating liner and inner baffle create a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.

4. 发明申请

US20020004003A1 Device for cooling a component subject to temperature stress of nonuniform intensity 失效
标题翻译：用于冷却不均匀强度的温度应力的部件的装置
公开(公告)号：US20020004003A1
公开(公告)日：2002-01-10
申请号：US09898174
申请日：2001-07-03
发明人： Emil Aschenbruck , Hildegard Ebbing , Klaus Dieter Mohr
IPC分类号： F01D025/12
CPC分类号： F01D25/12 , F01D9/023 , F01D11/24 , F05D2260/201
摘要： A symmetrical component of a turbine unit, whose wall is exposed to a hot medium on one side and is subject to nonuniform thermal stress over the circumference, is cooled by a flow of cooling air being guided along the other side of the component. A ring (5) is provided with slots (7) or other openings for the passage of the cooling air. The ring (5) protrudes into the flow of the cooling air. The overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to the higher stress is larger than the overall cross section of the slots (7) that are arranged in the sections of the ring (5) that are adjacent to the areas of the component that are subject to a lower stress.
摘要翻译：涡轮单元的对称部件，其壁暴露于一侧的热介质并且在圆周上受到不均匀的热应力，由沿组件的另一侧引导的冷却空气流冷却。环（5）设置有用于冷却空气通过的狭槽（7）或其他开口。环（5）突出到冷却空气的流中。布置在环（5）的与受到较高应力的部件的区域相邻的部分中的槽（7）的整个横截面大于槽（7）的整个横截面），其布置在环（5）的与受到较低应力的部件的区域相邻的部分中。

5. 发明申请

US20040062644A1 INTERNALLY MOUNTED RADIAL FLOW INTERCOOLER FOR A ROTARY COMPRESSOR MACHINE 失效
标题翻译：用于旋转式压缩机的内部径向流动介质
公开(公告)号：US20040062644A1
公开(公告)日：2004-04-01
申请号：US10256863
申请日：2002-09-27
发明人： Steven P. Meshenky
IPC分类号： F01D025/12
CPC分类号： F04D29/5826 , F01D25/12 , F04D17/12 , F04D25/04 , Y02T50/675
摘要： Improved efficiency is obtained in a rotary machine having a rotary shaft (18) mounting a compressor wheel (20) that discharges into a heat exchanger (36) having a core (82) with a central opening (42) in surrounding relation to the shaft (18). The heat exchanger (36) includes a coolant tank (90) on one side of the core (82) and in fluid communication with the same which serves as one boundary of radially extending space (68) through which a gas is discharged by a compressor wheel (20). A deswirling vane structure (80) causes gas discharged by the compressor wheel (22) to move radially outward within the space (68) and is formed of a material of good thermal conductivity and thermally bridged to the tank (90) to conduct heat thereto to be rejected to coolant in the tank.
摘要翻译：在具有安装压缩机叶轮（20）的旋转轴（18）的旋转机器中获得了提高的效率，该压缩机叶轮（20）排放到具有芯部（82）的热交换器（36）中，该中心开口（42）围绕轴（18）。热交换器（36）包括在芯部（82）的一侧上的流体连通的冷却剂罐（90），其作为径向延伸空间（68）的一个边界流体连通，气体通过压缩机轮（20）。旋转叶片结构（80）使得由压缩机叶轮（22）排出的气体在空间（68）内径向向外移动，并且由具有良好导热性的材料形成并热桥接到罐（90）以将热量传导到被拒绝在坦克中的冷却液。

6. 发明申请

US20030161716A1 Method of forming a thermally isolated gas turbine engine housing 有权
标题翻译：形成热隔离燃气涡轮发动机壳体的方法
公开(公告)号：US20030161716A1
公开(公告)日：2003-08-28
申请号：US10084858
申请日：2002-02-25
申请人： Honeywell International, Inc.
发明人： Ly D. Nguyen , Louis Cruse , Ivar Gene Fowkes , Silvestre Salas , William North , Vadanth Kadambi
IPC分类号： F01D025/12
CPC分类号： F01D9/065 , F01D25/14
摘要： A method for forming a thermally isolating gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is positioned within the turbine housing with an outer baffle arranged about the floating liner and an inner baffle arranged within the floating liner. The inner and outer baffles are welled or brazed to the floating liner assembly to form a unitary assembly creating a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.
摘要翻译：一种用于从与流过壳体的燃烧气体相关联的显着高温形成隔热燃气涡轮机壳体的方法。浮动衬套定位在涡轮机壳体内，其中外挡板布置在浮动衬套周围，并且内挡板布置在浮动衬套内。内挡板和外挡板被精加工或钎焊到浮动衬套组件以形成整体组件，其在壳体内形成单个连续的冷却通道，用于从相邻的浮动衬套的表面收集热量并将热量排出到燃烧废气流中。

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