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1. 发明申请

US20100272953A1 COOLED HYBRID STRUCTURE FOR GAS TURBINE ENGINE AND METHOD FOR THE FABRICATION THEREOF 审中-公开
标题翻译：用于气体涡轮发动机的冷却混合结构及其制造方法
公开(公告)号：US20100272953A1
公开(公告)日：2010-10-28
申请号：US12431547
申请日：2009-04-28
申请人： Paul Yankowich , James Hadder
发明人： Paul Yankowich , James Hadder
IPC分类号： B32B3/24 , B05D3/12
CPC分类号： F23M5/085 , F23M2900/05004 , F23R3/007 , F23R3/06 , F23R2900/03041 , F23R2900/03044 , Y10T428/24331
摘要： A cooled hybrid structure is provided for deployment within a gas turbine engine. In one embodiment, the cooled hybrid structure includes a woven oxide fiber sheet and an insulative oxide coating. The woven oxide fiber sheet includes an outer cold wall and an inner hot wall, which is integrally woven with the outer cold wall and which cooperates therewith to define a plurality of elongated cooling channels extending within the woven oxide fiber sheet. A plurality of impingement apertures is formed through the outer cold wall and conducts airflow into the plurality of elongated cooling channels and against the inner hot wall to convectively cool the woven oxide fiber sheet. A plurality of effusion channels is formed through the inner hot wall and through the insulative oxide coating and conducts airflow through the insulative oxide coating to provide convective cooling thereof.
摘要翻译：提供冷却的混合结构用于部署在燃气涡轮发动机内。在一个实施方案中，冷却的混合结构包括氧化纤维织物片和绝缘氧化物涂层。编织氧化物纤维片材包括外部冷壁和内部热壁，其与外部冷壁整体编织并与之配合，以限定在机织氧化物纤维片材内延伸的多个细长的冷却通道。通过外部冷壁形成多个冲击孔，并将气流传导到多个细长的冷却通道中并抵靠内部热壁以对流地冷却机织氧化物纤维片材。通过内部热壁和绝缘氧化物涂层形成多个渗出通道，并且通过绝缘氧化物涂层传导气流以提供其对流冷却。

2. 发明申请

US20050056020A1 Tube cooled combustor 失效
标题翻译：管冷却燃烧器
公开(公告)号：US20050056020A1
公开(公告)日：2005-03-17
申请号：US10648937
申请日：2003-08-26
申请人： James Hadder
发明人： James Hadder
IPC分类号： F02C1/00 , F23R3/00
CPC分类号： F23R3/005 , Y02T50/675
摘要： An innovative cooling tube assembly is disclosed for use in cooling the liner of a combustor in a gas turbine engine. Each cooling tube has a serpentine shape that conforms to the contour of the liner as the tube extends from one end of the combustor to the other to conduct cooling air in a counterflow direction to the exhaust gases. The cooling air gains heat, thereby cooling the liner wall, and is delivered in the proximity of the burners where its heat aids in combustion. An assembly of cooling tubes is provided for mounting on either the cool side or the hot side of the combustor liner, the assembly comprising a plurality of nested cooling tubes. The cooling tubes may be fabricated of a metallic material and either brazed to the liner or supported by pins inserted through the liner. The cooling tubes may also be fabricated of a CMC material by an innovative method in which an expendable mandrel of the desired cooling tube shape is inserted into one or more sleeves of a woven tubular fabric bound to a fabric shell formed in the shape of the combustor liner and densified in a furnace.
摘要翻译：公开了一种用于冷却燃气涡轮发动机中的燃烧器的衬套的创新的冷却管组件。当管从燃烧器的一端延伸到另一端时，每个冷却管具有符合衬套轮廓的蛇形形状，从而以与排气相反的方向导入冷却空气。冷却空气获得热量，从而冷却衬套壁，并在燃烧器附近被输送，其中有助于燃烧。提供冷却管的组件，用于安装在燃烧器衬套的冷侧或热侧上，该组件包括多个嵌套冷却管。冷却管可以由金属材料制成，并且钎焊到衬套上或者通过插入衬套的销支撑。冷却管也可以通过创新的方法由CMC材料制成，其中将所需冷却管形状的消耗性心轴插入结合到形成为燃烧器形状的织物外壳的编织管状织物的一个或多个套筒中衬里并在炉中致密化。

3. 发明申请

US20050100441A1 Thermally stabilized turbine scroll retention ring for uniform loading application 失效
标题翻译：用于均匀加载应用的热稳定型涡轮涡旋保持环
公开(公告)号：US20050100441A1
公开(公告)日：2005-05-12
申请号：US10712434
申请日：2003-11-12
申请人： Ly Nguyen , James Hadder , Gregory Woodcock , Stony Kujala
发明人： Ly Nguyen , James Hadder , Gregory Woodcock , Stony Kujala
IPC分类号： F01D9/02 , F01D9/04 , F01D1/02
CPC分类号： F01D9/026 , F01D9/045 , F05D2230/642
摘要： A turbine scroll retention ring may comprise a retainer ring, a plurality of ring fingers, and a plurality of ring joggles. The turbine scroll retention ring may surround and be attached to a radial nozzle. The ring joggles may allow for thermal growth variations between the radial nozzle and the turbine scroll retention ring. The radially outer end portions of the ring fingers may be in contact with a turbine scroll component (for example, an aft scroll ring), such that the turbine scroll retention ring may force contact between the turbine scroll component and the radial nozzle. The finger joggles of the ring fingers may allow for thermal growth variations between the radial nozzle and the turbine scroll component. The turbine scroll retention ring may provide constant axial loading to the aft scroll ring during all engine operating conditions.
摘要翻译：涡轮机涡旋保持环可以包括保持环，多个无名指和多个环形滑轨。涡轮机涡旋保持环可围绕并附接到径向喷嘴。环形滑轨可以允许径向喷嘴和涡轮涡旋保持环之间的热生长变化。环形指状物的径向外端部分可以与涡轮机涡旋部件（例如，后涡旋环）接触，使得涡轮涡旋保持环可以迫使涡轮机涡旋部件和径向喷嘴之间的接触。环形指状物的手指可以允许径向喷嘴和涡轮机涡旋部件之间的热生长变化。涡轮机涡旋保持环可以在所有发动机操作条件期间为后涡旋环提供恒定的轴向负载。

4. 发明申请

US20070234725A1 Counterbalanced fuel slinger in a gas turbine engine 审中-公开
标题翻译：燃气涡轮发动机中的平衡燃料抛油环
公开(公告)号：US20070234725A1
公开(公告)日：2007-10-11
申请号：US11393580
申请日：2006-03-29
申请人： Ian Critchley , James Hadder
发明人： Ian Critchley , James Hadder
IPC分类号： F02C7/22
CPC分类号： F23R3/38 , F23R3/52 , F23R2900/00005
摘要： A rotary fuel slinger and a turbine engine including the rotary fuel source is provided. The rotary fuel slinger includes a coupler shaft coupled to a turbine shaft of the turbine engine and is configured to rotate therewith. The slinger further includes a slinger disc coupled to the coupler shaft and configured to rotate therewith. The slinger disc includes a vertical shoulder extending substantially perpendicular to the coupler shaft and a slinger disc rim extending substantially perpendicularly from the vertical shoulder. The slinger disc rim is configured to define a cup-shaped section and a counterbalance mass, wherein the cup-shaped section is counterbalanced by the counterbalance mass. The rotary fuel slinger is adapted to receive a rotational drive force and to receive a flow of fuel from a fuel source and configured, upon receipt of the rotational drive force, to centrifuge the received fuel into a combustion chamber of the turbine engine.
摘要翻译：提供旋转燃料抛油环和包括旋转燃料源的涡轮发动机。旋转燃料抛油环包括联接到涡轮发动机的涡轮轴的联轴器，并且构造成与其一起旋转。抛油环还包括联接到联接轴并且被配置为随其旋转的抛油盘。抛油盘包括基本上垂直于联接轴延伸的垂直肩部和从垂直肩部基本上垂直延伸的抛油环盘缘。抛油环盘缘被配置为限定杯形部分和平衡块，其中杯形部分由平衡块抵消。旋转燃料抛油环适于接受旋转驱动力并且接收来自燃料源的燃料流并且在接收到旋转驱动力时构造成将接收到的燃料离心到涡轮发动机的燃烧室中。

5. 发明申请

US20060053798A1 Waffled impingement effusion method 失效
标题翻译：华氏冲击渗流法
公开(公告)号：US20060053798A1
公开(公告)日：2006-03-16
申请号：US10938805
申请日：2004-09-10
申请人： James Hadder
发明人： James Hadder
IPC分类号： F23R3/42
CPC分类号： F23R3/007 , F23R2900/00017 , F23R2900/03044 , Y02T50/67 , Y02T50/675
摘要： A combined impingement effusion method comprises brazing or welding a waffled impingement plate to the cold back-side surface of component having effusion holes there through. The impingement plate comprises a plurality of small baffle cells to relieve the thermal stresses between the impingement plate and the component. By rigidly attaching the impingement plate, the cooling flow leakage associated with the seals of floating plates is avoided.
摘要翻译：组合冲击渗流法包括将瓦楞冲击板钎焊或焊接到其中具有渗出孔的部件的冷背侧表面。冲击板包括多个小的挡板单元，以减轻冲击板和部件之间的热应力。通过刚性地附接冲击板，避免了与浮板的密封件相关联的冷却流动泄漏。

6. 发明申请

US20060067813A1 Compliant mounting system for turbine shrouds 有权
标题翻译：符合涡轮机罩的安装系统
公开(公告)号：US20060067813A1
公开(公告)日：2006-03-30
申请号：US10950750
申请日：2004-09-27
申请人： Adrian Allan , James Hadder , George Zurmehly
发明人： Adrian Allan , James Hadder , George Zurmehly
IPC分类号： F01D25/26
CPC分类号： F01D9/02 , F01D25/246 , F01D25/26 , F05D2240/11 , Y10T29/4932 , Y10T29/49323 , Y10T29/49863 , Y10T29/49874
摘要： The mounting of low expansion full ring shrouds in a turbine engine requires radial compliance to limit the stresses experienced by the shroud due to thermal growth differences between the shroud and its support. The present invention provides a method of providing radial compliance with no looseness in the mounting system. The compliant mounting system of the present invention also allows for axial motion of the shroud, should such motion be needed or desired. The lack of looseness in the shroud mounting system of the present invention results in an ability to achieve smaller tip clearances and thus better engine performance.
摘要翻译：在涡轮发动机中安装低膨胀全环护罩需要径向顺应性，以限制由于护罩和其支撑件之间的热膨胀差异导致的护罩所经受的应力。本发明提供了一种在安装系统中提供没有松动的径向顺应性的方法。如果需要或期望这样的运动，本发明的柔性安装系统还允许护罩的轴向运动。在本发明的护罩安装系统中缺乏松动性导致能够实现更小的尖端间隙，从而获得更好的发动机性能。

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