摘要:
A turbine component, such as a turbine blade having a metal substrate (22) is coated with a metal MCrAlY alloy layer (24) and then a thermal barrier layer (20) selected from LaAlO3, NdAlO3, La2Hf2O7, Dy3Al5O12, HO3Al3O12, ErAlO3, GdAlO3, Yb2Ti2O7, LaYbO3, Gd2Hf2O7 or Y3Al5O12.
摘要翻译:涡轮机部件,例如具有金属基体(22)的涡轮机叶片涂覆有金属MCrAlY合金层(24),然后涂覆选自LaAlO 3,NdAlO 3,La 2 Hf 2 O 7,Dy 3 Al 5 O 12,HO 3 Al 3 O 12,ErAlO 3, GdAlO 3,Yb 2 Ti 2 O 7,LaYbO 3,Gd 2 Hf 2 O 7或Y 3 Al 5 O 12。
摘要:
The present invention generally describes multilayer thermal barrier coating systems and methods of making the multilayer thermal barrier coating systems. The thermal barrier coating systems comprise a first ceramic layer, a second ceramic layer, a thermally grown oxide layer, a metallic bond coating layer and a substrate. The thermal barrier coating systems have improved high temperature thermal and chemical stability for use in gas turbine applications.
摘要:
The present invention generally describes multilayer coating systems comprising a composite metal/metal oxide bond coat layer. The coating systems may be used in gas turbines.
摘要:
The present invention generally describes methods for modifying MCrAlY coatings by using gaseous carburization, gaseous nitriding or gaseous carbonitriding. The modified MCrAlY coatings are useful in thermal barrier coating systems, which may be used in gas turbine engines.
摘要:
A turbine component contains a substrate (22) such as a superalloy, a basecoat (24) of the type MCrAlY, and a continuous barrier layer (28) between the substrate and basecoat, where the barrier layer (28) is made of an alloy of (Re, Ta, Ru, Os)X, where X can be Ni, Co or their mixture, where the barrier layer is at least 2 micrometers thick and substantially prevents materials from both the basecoat and substrate from migrating through it.
摘要:
A thermal barrier coating for hot gas path components of a combustion turbine based on a zirconia-scandia system. A layer of zirconium scandate having the hexagonal Zr3Sc4O12 structure is formed directly on a superalloy substrate or on a bond coat formed on the substrate.
摘要翻译:一种用于基于氧化锆 - Scandia系统的燃气轮机的热气路径部件的热障涂层。 具有六方晶Zr 3 Sc 4 O 12结构的钪酸钪层直接形成在超合金基板上或形成在基板上的接合涂层上。
摘要:
A substrate (12) such as a superalloy turbine component is coated with a basecoat (14) of the type MCrAlY which also contains boron, where the amount of boron in the basecoat is in a concentration gradient where more boron is present near the top (16) than the bottom (20) of the basecoat (14) and boron is present in an average amount of over 0.50 wt. % throughout the basecoat cross-section (14) of the composite (10).
摘要:
A wash-coat (16) for use as a support for an active catalyst species (18) and a catalytic combustor component (10) incorporating such wash-coat. The wash-coat is a solid solution of alumina or alumina-based material (Al2O3-0-3 wt % La2O3) and a further oxide exhibiting a coefficient of thermal expansion that is lower than that exhibited by alumina. The further oxide may be silicon dioxide (2-30 wt % SiO2), zirconia silicate (2-30 wt % ZrSiO4), neodymium oxide (0-4 wt %), titania (Al2O3-3-40% TiO2) or alumina-based magnesium aluminate spinel (Al2O3-25 wt % MgO) in various embodiments. The active catalyst species may be palladium and a second metal in a concentration of 10-50% of the concentration of the palladium.
摘要翻译:用作活性催化剂种类(18)和催化燃烧器组分(10)的载体的洗涂层(16),其结合有这种洗衣层。 洗涤涂层是氧化铝或氧化铝基材料(Al 2 O 3 -0-3重量%La 2 O 3)的固溶体和表现出比氧化铝表现出的热膨胀系数更高的氧化物。 另外的氧化物可以是二氧化硅(2-30重量%SiO 2),氧化硅硅酸盐(2-30重量%ZrSiO 4),氧化钕(0-4重量%),二氧化钛(Al 2 O 3 -3-40%TiO 2)或氧化铝 - 铝酸镁尖晶石(Al2O3-25wt%MgO)。 活性催化剂种类可以是钯,浓度为钯浓度的10-50%的第二种金属。
摘要:
A component for use in a combustion turbine (10) is provided that includes a substrate (212) and an abradable coating system (216) deposited on the substrate (212). A planar proximity sensor (250) may be deposited beneath a surface of the abradable coating system (216) having circuitry (252) configured to detect intrusion of an object (282) into the abradable coating system (216). A least one connector (52) may be provided in electrical communication with the planar proximity sensor (250) for routing a data signal from the planar proximity sensor (250) to a termination location (59). A plurality of trenches (142) may be formed at respective different depths below the surface of the abradable coating system (216) with a planar proximity sensor (250) deposited within each of the plurality of trenches (142). A processing module (34) may be programmed for receiving data from the planar proximity sensor (250) and calculating a clearance between a row of blades (18,19) within a combustion turbine and the planar proximity sensor (250). The processing module (34) may control a clearance between the row of blades (18) and a ring segment (284) based on data received from the planar proximity sensors (250).
摘要:
Aspects of the invention relate to a system for monitoring the wear of a component. A conductor can be embedded in the component at a depth from a surface of the component. In one embodiment, the conductor can be operatively connected to a power source to form an electrical circuit. The resistance across the conductor can be measured. As the component contacts a second component, the component can begin to wear. Once the wear progresses to the conductor, changes in the measured resistance can result. Thus, an operator can be alerted that the component has worn to a certain point and that service may be needed. Alternatively, impedance can be measured across the conductor. Because the dielectric permeability of the material surrounding the conductor can affect impedance, changes in impedance can occur as the surface material of the component is worn away.