Abstract:
A process includes forming a printed article having an external surface and at least one microfeature with an internal surface by additive manufacture, coating the external surface and the internal surface of the printed article with a metallic microlayer to form a coated article, and densifying the coated article to form a component. After formation, the printed article has a porosity such that the printed article is not at full density. A densified component includes a printed article having an external surface and at least one microfeature with an internal surface and a metallic microlayer coating the external surface and the internal surface of the printed article. The printed article is formed by additive manufacture.
Abstract:
A treatment composition is disclosed including a carrier and a sacrificial oxide-forming material suspended within the carrier. The sacrificial oxide-forming material is selected from the group consisting of tin oxide, magnesium oxide, antimony pentaoxide, and combinations thereof. A treatment process for a gas turbine component including an abradable ceramic coating is disclosed. The process includes contacting the abradable ceramic coating with the treatment composition. The sacrificial oxide-forming material is infused into the abradable ceramic coating to form sacrificial oxide-forming deposits within the abradable ceramic coating. A rejuvenation process is disclosed including contacting the hot gas path surface of a gas turbine component with a rinse composition comprising water and the treatment composition to form the sacrificial oxide-forming deposits within the abradable ceramic coating.
Abstract:
A coating, a coating system, and a coating method are provided. The coating includes between about 0.25-35% filler particles embedded in a chrome phosphate binder matrix comprising a balance of the coating by volume. The filler particles have a size in the range from nanosize to six microns with an aspect ratio of from 1:1 to 3:1, and include up to 100% by weight lubricious particles with a balance hard particles. The lubricious particles are selected from the group consisting of boron nitride (BN), titanium nitride (TiN), titanium oxide (TiO2), zinc (Zn), tin (Sn), oxides of zinc and tin, and combinations thereof. The hard particles are selected from the group consisting of chromium carbide (CrC), tungsten carbide (WC), silicon (Si), aluminum (Al), oxides or nitrides of silicon and aluminum, and combinations thereof. A green slurry coating includes an evaporable solvent mixed with the filler particles and chrome phosphate binder matrix.
Abstract:
An abradable seal having a metallic substrate and a multi-layered ceramic coating on the metallic substrate. The multi-layered ceramic coating includes a base layer deposited on the metallic substrate, an abradable layer overlaying the first layer, and an abrading layer overlaying the second layer. The abrading layer is formed of an abrading material. A turbine system and a method for forming an abradable seal are also disclosed.
Abstract:
A thermal barrier coating system for metal components in a gas turbine engine having an ultra low thermal conductivity and high erosion resistance, comprising an oxidation-resistant bond coat formed from an aluminum rich material such as MCrAlY and a thermal insulating ceramic layer over the bond coat comprising a zirconium or hafnium oxide lattice structure (ZrO2 or HfO2) and an oxide stabilizer compound comprising one or more of the compounds ytterbium oxide (Yb2O3), yttria oxide (Y2O3), hafnium oxide (HfO2), lanthanum Oxide (La2O3), tantalum oxide (Ta2O5) or zirconium oxide (ZrO2). The invention includes a new method of forming the ceramic-based thermal barrier coatings using a liquid-based suspension containing microparticles comprised of at least one of the above compounds ranging in size between about 0.1 and 5 microns. The coatings form a tortuous path of ceramic interfaces that increase the coating toughness while preserving the ultra low thermal conductivity.
Abstract translation:一种用于具有超低热导率和高耐侵蚀性的燃气轮机中的金属部件的隔热涂层系统,包括由富铝材料如MCrAlY形成的抗氧化粘合涂层和粘结涂层上的绝热陶瓷层 包括锆或铪氧化物晶格结构(ZrO 2或HfO 2)和包含一种或多种化合物氧化镱(Yb 2 O 3),氧化钇(Y 2 O 3),氧化铪(HfO 2),氧化镧(La 2 O 3),钽 氧化物(Ta2O5)或氧化锆(ZrO2)。 本发明包括使用包含由至少一种上述化合物构成的微粒的液体基悬浮液形成陶瓷基热障涂层的新方法,其尺寸范围为约0.1至5微米。 涂层形成陶瓷界面的曲折路径,从而提高涂层韧性,同时保持超低热导率。
Abstract:
A cleaning method and a cleaning fluid are provided. The cleaning method includes accessing a plurality of turbine components attached to a turbine assembly, the turbine assembly being a portion of a turbomachine, positioning at least one cleaning vessel over at least one of the turbine components, forming a liquid seal with a sealing bladder, providing a cleaning fluid to the cleaning vessel, and draining the cleaning fluid from the cleaning vessel. The cleaning fluid includes a carrier fluid and a solvent additive for removing fouling material from the turbine component. An alternative cleaning method is also provided.
Abstract:
A coating method, coated article and coating are provided. The coated article includes a low temperature component, and a graphene coating formed from a graphene derivative applied over the low temperature component. The coating method includes providing a graphene derivative, providing a low temperature component, applying the graphene derivative over the low temperature component, and forming a graphene coating. The graphene coating reduces corrosion and fouling of the low temperature component. The coating includes a graphene derivative, and modified functional groups on the graphene derivative. The modified functional groups increase adherence of the coating on application to a low temperature component.