摘要:
A method for providing a component with protection against sand related distress comprises the steps of: providing a substrate; and forming a thermal barrier coating system by depositing at least one layer of a first material selected from the group consisting of a zirconate, a hafnate, a titanate, and mixtures thereof, which first material has been mixed with at least one oxide so that each layer contains from about 25 to 99 wt% of at least one oxide.
摘要:
A metallic coating for use in a high temperature application is created from a nickel base alloy containing from 5.0 to 10.5 wt % aluminum, from 4.0 to 15 wt % chromium, from 2.0 to 8.0 wt % tungsten, from 3.0 to 10 wt % tantalum, and the balance nickel. The metallic coating has particular utility in protecting single crystal superalloys used in high temperature applications such as turbine engine components.
摘要:
A thermal barrier coating system for use on a turbine engine component which reduces sand related distress is provided. The coating system comprises at least one first layer of a stabilized material selected from the group consisting of zirconia, hafnia, and titania and at least one second layer containing at least one of oxyapatite and garnet. Where the coating system comprises multiple first layers and multiple second layers, the layers are formed or deposited in an alternating manner.
摘要:
A thermal barrier coating system for use on a turbine engine component which reduces sand related distress is provided. The coating system comprises at least one first layer of a stabilized material selected from the group consisting of zirconia, hafnia, and titania and at least one second layer containing at least one of oxyapatite and garnet. Where the coating system comprises multiple first layers and multiple second layers, the layers are formed or deposited in an alternating manner.
摘要:
A turbine engine component is provided which has a substrate and a thermal barrier coating applied over the substrate. The thermal barrier coating comprises at least one layer of a first material selected from the group consisting of a zirconate, a hafnate, a titanate, and mixtures thereof, which first material has been mixed with, and contains, from about 25 to 99 wt % of at least one oxide. The at least one oxide comprises at least one oxide of a material selected from the group consisting of lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, scandium, indium, and yttrium. If desired, a metallic bond coat may be present between the substrate and the thermal barrier coating system. A method for forming the thermal barrier coating system of the present invention is described.
摘要:
A process for coating a part comprises the steps of providing a chamber which is electrically connected as an anode, placing the part to be coated in the chamber, providing a cathode formed from a coating material to be deposited and platinum, and applying a current to the anode and the cathode to deposit the coating material and the platinum on the part.
摘要:
A process for coating a part comprises the steps of providing a chamber which is electrically connected as an anode, placing the part to be coated in the chamber, providing a cathode formed from a coating material to be deposited and platinum, and applying a current to the anode and the cathode to deposit the coating material and the platinum on the part.
摘要:
A turbine engine component has a substrate and a thermal barrier coating deposited onto the substrate. The thermal barrier coating comprises a ceramic material having a sodium containing compound incorporated therein. The sodium containing compound is present in a concentration so that when molten sand reacts with the coating, sodium silicate is formed as the by product.
摘要:
A turbine engine component is provided which has a substrate, a yttria-stabilized zirconia coating applied over the substrate, and a molten silicate resistant outer layer. The molten silicate resistant outer layer is formed from gadolinia or gadolinia-stabilized zirconia. A method for forming the coating system of the present invention is described.
摘要:
A thermal barrier coating system for use on a turbine engine component which reduces sand related distress is provided. The coating system comprises at least one first layer of a stabilized material selected from the group consisting of zirconia, hafnia, and titania and at least one second layer containing at least one of oxyapatite and garnet. Where the coating system comprises multiple first layers and multiple second layers, the layers are formed or deposited in an alternating manner.