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公开(公告)号：US20150069020A1
公开(公告)日：2015-03-12
申请号：US14482873
申请日：2014-09-10
IPC分类号： H01H33/10
CPC分类号： H01H33/10 , C23C4/08 , H01B1/02 , H01H1/02372 , H01H1/025 , H01H11/048 , H01H2001/0208 , H01H2201/024 , H01H2201/026 , H01H2201/03 , H01H2239/044 , H01H2300/036
摘要： A contact element for high voltage direct current switches includes a matrix made of a first material selected from the group comprising copper, silver, palladium, platinum, tungsten, molybdenum, rhenium, nickel, gold, and alloys thereof. The contact element also includes a foreign phase, which is dispersed in the matrix and is made of a second material selected from the group comprising carbon, tin(II) oxide, tin(IV) oxide, zinc(II) oxide, tungsten, nickel and mixtures thereof. The contact element has a porosity of ≦1.0% by volume, based on a total volume of the contact element.
摘要翻译： 用于高压直流开关的接触元件包括由选自铜，银，钯，铂，钨，钼，铼，镍，金及其合金的第一材料制成的基体。 接触元件还包括异相，其分散在基质中并且由选自碳，氧化锡（II），氧化锡（IV），氧化锌（II），钨，镍的组中的第二材料制成 及其混合物。 基于接触元件的总体积，接触元件的孔隙率为＆lt; lEE; 1.0体积％。
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公开(公告)号：US20170002667A1
公开(公告)日：2017-01-05
申请号：US15198915
申请日：2016-06-30
发明人： Juergen STEINWANDEL , Ning WANG , Helmut PIRINGER
CPC分类号： F01D5/282 , B28B1/24 , B28B11/243 , C04B35/053 , C04B35/117 , C04B35/486 , C04B35/505 , C04B35/62857 , C04B35/6286 , C04B35/62863 , C04B35/62865 , C04B35/62894 , C04B35/62897 , C04B35/6348 , C04B35/76 , C04B35/803 , C04B2235/5244 , C04B2235/5248 , C04B2235/614 , C04B2235/616 , C23C16/045 , C23C16/30 , C23C16/32 , C23C16/442 , F01D5/284 , F01D5/288 , F05D2220/32 , F05D2230/90 , F05D2300/2112 , F05D2300/2118 , F05D2300/226 , F05D2300/228 , F05D2300/44 , F05D2300/601 , F05D2300/6033
摘要： This relates to a turbine blade comprising a preformed fibrous fabric of fibres consisting of carbon, silicon carbide or rhenium fixed with a binder resin, and wherein the preformed and fixed fibrous fabric is coated and infiltrated, respectively, with B4C, wherein the preformed fibrous fabric that has been fixed and coated and infiltrated, respectively, with B4C further has a multilayer coating consisting of at least one layer of silicon carbide and at least one layer of a metal boride, a metal nitride or a metal carbide, and wherein an oxide ceramic is applied over the multilayer coating. The turbine blade is resistant to high temperatures and is particularly well suited for use in a gas turbine. Methods for producing the turbine blade are also described.
摘要翻译： 这涉及一种涡轮叶片，其包括由碳，碳化硅或铼固定的纤维组成的纤维织物预先形成的纤维织物，所述纤维织物用粘合剂树脂固定，并且其中预先形成的和固定的纤维织物分别用B4C涂覆和渗透，其中预成型纤维织物 已经用B4C分别固定和涂覆和渗透的多层涂层进一步具有由至少一层碳化硅和至少一层金属硼化物，金属氮化物或金属碳化物组成的多层涂层，并且其中氧化物陶瓷 施加在多层涂层上。 涡轮叶片耐高温，特别适用于燃气轮机。 还描述了用于生产涡轮叶片的方法。
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公开(公告)号：US20170129798A1
公开(公告)日：2017-05-11
申请号：US15413500
申请日：2017-01-24
IPC分类号： C03B23/13 , C03C17/22 , F24J2/05 , C03B23/043
CPC分类号： C03B23/13 , C03B23/043 , C03C17/22 , C03C2217/285 , C03C2217/732 , C03C2218/15 , F24S10/45 , Y02E10/44
摘要： This disclosure relates to a method and an apparatus for sealing a double-walled glass tube in a vacuum-tight manner, in particular a production method for manufacturing of solar collectors. By means of a vacuum chamber, inside of which a holding element is fixed and inside of which a heating conductor is arranged, an electro-conductively heating and a subsequent deforming of the double-walled glass tube can be achieved. No additional materials, such as metallic auxiliary element, solders are required. A simple installation inside the vacuum chamber is possible and a minimum vacuum feedthrough for the power supply of a heating conductor is required. The direct heat transfer onto the double walled glass tube and a resulting quick process control allows to reliably seal a double-walled glass tube of a thermal solar collector under vacuum with simple means.
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公开(公告)号：US20170081033A1
公开(公告)日：2017-03-23
申请号：US15272988
申请日：2016-09-22
IPC分类号： B64D15/12 , C23C16/44 , C23C16/02 , B05D3/02 , C23C16/34 , C23C16/32 , C23C16/38 , B05D1/22 , C23C16/40
CPC分类号： B64D15/12 , B05D1/22 , B05D3/0218 , C23C16/0218 , C23C16/325 , C23C16/342 , C23C16/38 , C23C16/403 , C23C16/44 , H05B3/145 , H05B3/22 , H05B2214/02
摘要： A heating element for in-flight de-icing of aircraft is disclosed. The heating element includes a carbon fiber material that is designed to be arranged on a component of an aircraft. The carbon fiber material includes at least two electrical contacts for connecting to an electrical wiring system, and at least one insulation layer for electrical insulation.
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