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公开(公告)号：US07600867B2
公开(公告)日：2009-10-13
申请号：US11382904
申请日：2006-05-11
CPC分类号： B41J2/01 , B41J3/407 , B41J11/002
摘要： A printing system that includes a source which emits UV radiation to polymerize a fluid that is deposited onto a substrate by one or more print heads. The source emits low energy UV radiation sufficient to set the fluid to a quasi-fluid, non-hardened state.
摘要翻译： 一种打印系统，其包括发射UV辐射以使由一个或多个打印头沉积到基底上的流体聚合的源。 源发射足够的能量UV辐射，以将流体设置为准流体，非硬化状态。
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公开(公告)号：US07073901B2
公开(公告)日：2006-07-11
申请号：US10172761
申请日：2002-06-13
IPC分类号： B41J2/01
CPC分类号： B41J2/01 , B41J3/407 , B41J11/002
摘要： A printing system that includes a source which emits UV radiation to polymerize a fluid that is deposited onto a substrate by one or more print heads. The source emits low energy UV radiation sufficient to set the fluid to a quasi-fluid, non-hardened state.
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3.发明授权Inkjet inks, methods for applying inkjet ink, and articles printed with inkjet inks 有权喷墨油墨，喷墨油墨的涂布方法以及用喷墨油墨印刷的物品公开(公告)号：US07919543B2
公开(公告)日：2011-04-05
申请号：US11353754
申请日：2006-02-14
申请人： Charles L. Beck , Stephen J. Mills
发明人： Charles L. Beck , Stephen J. Mills
CPC分类号： C09D11/101
摘要： Compositions for inkjet inks, methods for applying the ink to a surface of a substrate, and articles that include indicia printed with the ink. The inkjet inks include a cellulose polymer and a liquid carrier. Unlike currently available commercial inks, the inkjet inks of this invention can be formulated with less toxic ingredients, thus reducing the risks of negative impact on environmental quality and the health and safety of workers who use the inks.
摘要翻译： 用于喷墨油墨的组合物，用于将油墨施加到基材表面的方法，以及包括用墨水印刷的标记的制品。 喷墨油墨包括纤维素聚合物和液体载体。 与现有的商业油墨不同，本发明的喷墨油墨可以配制成毒性较小的成分，从而降低对使用油墨的工人的环境质量以及健康和安全的负面影响的风险。
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公开(公告)号：US20100251722A1
公开(公告)日：2010-10-07
申请号：US11653407
申请日：2007-01-16
IPC分类号： F02C7/18
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/675
摘要： A combustor wall element arrangement for a gas turbine engine comprises an upstream wall element (50A) overlapping a downstream wall element (50B) and defining a gap (37) and an outlet (35) therebetween. In use, a coolant flow exits the outlet (35) to provide a coolant film (D) across at least a part of the downstream wall element (50B). The outlet (35) has a smaller dimension, normal to the downstream wall element (50B), than the gap (37) thereby increasing the velocity of the coolant flow across at the downstream wall element (50B). The resultant film coolant flow is effective further across the downstream wall element.
摘要翻译： 用于燃气涡轮发动机的燃烧器壁元件装置包括与下游壁元件（50B）重叠并在其间限定间隙（37）和出口（35）的上游壁元件（50A）。 在使用中，冷却剂流离开出口（35）以在穿过下游壁元件（50B）的至少一部分提供冷却剂膜（D）。 出口（35）比间隙（37）具有与下游壁元件（50B）垂直的较小的尺寸，从而增加在下游壁元件（50B）处的冷却剂流的速度。 所得薄膜冷却剂流动在下游壁元件进一步有效。
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5.发明授权Gas turbine engine with turbine tip clearance control device and method of operation 失效带涡轮顶端间隙控制装置的燃气轮机和操作方法
公开(公告)号：US5064343A
公开(公告)日：1991-11-12
申请号：US552133
申请日：1990-07-13
申请人： Stephen J. Mills
发明人： Stephen J. Mills
摘要： The problem of excessive clearances being generated by rub occurring between the tips of turbine blades and the linings on shroud segments which surround the blades is addressed by way of providing a valve 42 of a metal of different coefficient of expansion than the shroud control ring 24. On ground running prior to take off of an associated aircraft, the valve diverts a cooling airflow away from the ring 24, thus causing it to run hot and expand radially. The shrouds 22 are thus moved away from the blade tips 40 and on take off, are sufficiently far away from the tips 42 as to avoid deep penetration of the lining 38 thereby. The higher temperature generated by take off affects the valve 40 and makes it expand rapidly, to open the cooling airflow paths to the ring 24 via the holes 46 and 50.
摘要翻译： 通过提供涡轮叶片的尖端和围绕叶片的护罩段上的衬里之间产生的过度间隙的问题通过提供具有与护罩控制环24不同的膨胀系数的金属的阀42来解决。 在起飞相关飞行器之前的地面运行中，阀将冷却气流从环24分离，从而使其运行热并径向膨胀。 因此，护罩22从叶片尖端40移开并且在脱离时离开顶部42足够远，以避免衬里38的深入穿透。 通过起飞产生的较高温度影响阀40并使其迅速膨胀，以经由孔46和50打开到环24的冷却气流路径。
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公开(公告)号：US20100229563A1
公开(公告)日：2010-09-16
申请号：US11650432
申请日：2007-01-08
IPC分类号： F02C7/12
CPC分类号： F23R3/002 , F23R3/06 , F23R2900/03042 , Y02T50/675
摘要： The invention relates to a wall element for a wall structure of a gas turbine engine combustor. The wall element has an inner, in use, hot surface, and an outer, in use, cooler surface. A plurality of projections is provided on the outer surface to facilitate heat transfer to a coolant flow. The wall element comprises a means to direct more coolant flow at a hot-spot on an adjacent tile than the remainder of the adjacent tile and thereby reducing the thermal gradient across the adjacent tile.
摘要翻译： 本发明涉及一种用于燃气涡轮发动机燃烧器的壁结构的壁元件。 壁元件具有内部，使用中的热表面和外部，在使用中较冷的表面。 在外表面上设置有多个突起以便于热传递到冷却剂流。 壁元件包括在邻近瓦片上的热点处引导更多的冷却剂流量的方式，而不是相邻瓦片的其余部分，从而降低相邻瓦片的热梯度。
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7.发明授权Seal assembly with new resin stabilized adhesive composition to bond an insert member to the elastomeric seal material 失效用新的树脂稳定的粘合剂组合物的密封组件将插入件粘合到弹性体密封材料上公开(公告)号：US06268056B1
公开(公告)日：2001-07-31
申请号：US09236931
申请日：1999-01-25
申请人： Stephen J. Mills
发明人： Stephen J. Mills
IPC分类号： B32B1508
CPC分类号： F16J15/328 , C08L83/00 , C08L2666/14 , C09J163/00 , C09J183/04 , C09J183/08 , C09K3/10 , C09K2200/0607 , C09K2200/0612 , C09K2200/0647 , F16J15/3284 , Y10T428/31522 , Y10T428/31529 , Y10T428/31667
摘要： In a seal assembly having a support member made of either metal or plastic, and an elastomeric sealing material bonded by an adhesive composition to said support member, said composition being an epoxy resin stabilized silane adhesive composition made up from the following materials in parts by volume, (a) 1 to 80 parts organosilane material, which also includes a silane coupling agent, and a hydrolyzing agent for the organosilane, (b) 0.5 to 70 parts epoxy resin material, which includes an amine curing agent for the epoxy resin, (c) 50 to 3000 parts of aqueous fluid carrier medium for the composition, (d) 0.05 to 20 parts of additive material selected from the group consisting of a surfactant material and a rust inhibitor material.
摘要翻译： 在具有由金属或塑料制成的支撑构件和由粘合剂组合物粘合到所述支撑构件的弹性体密封材料的密封组件中，所述组合物是由以下材料以体积分数组成的环氧树脂稳定的硅烷粘合剂组合物 ，（a）1〜80份也包含硅烷偶联剂的有机硅烷材料和有机硅烷用水解剂，（b）含有环氧树脂的胺固化剂的0.5〜70份环氧树脂材料（ c）组合物的水性载体介质的50〜3000份，（d）选自表面活性剂材料和防锈材料的添加剂0.05〜20份。
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公开(公告)号：US5351732A
公开(公告)日：1994-10-04
申请号：US78218
申请日：1993-06-22
CPC分类号： F01D11/24
摘要： A gas turbine engine includes a casing cooling system which operates in one of two conditions, the first being operational at engine cruise, where all of the cooling air is initially directed onto a specific region of the casing; under full power conditions, some of the cooling air is directed onto the specific casing region and the reminder directed onto the reminder of the casing; the cooling system operates to optimize turbine blade/casing radial clearances.
摘要翻译： PCT No.PCT / GB91 / 01964 Sec。 371日期：1993年6月22日 102（e）日期1993年6月22日PCT 1991年11月8日PCT PCT。 公开号WO92 / 11444 日期：1992年7月9日。一种燃气涡轮发动机包括壳体冷却系统，其在两个条件之一中操作，第一个在发动机巡航时操作，其中所有冷却空气最初被引导到壳体的特定区域; 在全功率条件下，一些冷却空气被引导到特定的壳体区域，并且提醒被引导到壳体的提醒上; 该冷却系统用于优化涡轮机叶片/壳体径向间隙。
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