摘要:
A coated seal slot system for turbomachinery includes a first turbine component comprising a first groove having at least one first coating attached to at least a portion of the first groove of the first turbine component, a second turbine component comprising a second groove having at least one second coating attached to at least a portion of the second groove of the second turbine component. The first and the second turbine components are disposable adjacent to each other with the first groove having the first coating and the second groove having the second coating together forming a coated seal slot extending across a gap between the first turbine component and the second turbine component. A seal is disposable in the coated seal slot and extendable across the gap between the first and the second turbine components and engageable with the first coating and the second coating to inhibit leakage of gas through the gap.
摘要:
A coated substrate is provided that can include a substrate defining a surface, and an abradable coating on the surface of the substrate. The abradable coating can comprise La2-xAxMo2-y-y′ WyBy′O9-δ forming a crystalline structure, where A comprises Li, Na, K, Rb, Cs, Sc, Y, Ce, Pr, Nd, Pm, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Th, Be, Mg, Ca, Sr, Ba, Cu, Bi, Cd, Zn, Ag, Au, Pt, Ir, Rh, Ru, Pd, or combinations thereof; 0
摘要:
Coating systems are provided for use on a CMC substrate, that can include: a bond coat on a surface of the CMC substrate; a first rare earth silicate coating on the bond coat; a sacrificial coating of a reinforced rare earth silicate matrix on the at least one rare earth silicate layer; a second rare earth silicate coating on the sacrificial coating; and an outer layer on the second rare earth silicate coating. The first rare earth silicate coating comprises at least one rare earth silicate layer, and the second rare earth silicate coating comprises at least one rare earth silicate layer. The sacrificial coating has a thickness of about 4 mils to about 40 mils. Methods are also provided for tape deposition of a sacrificial coating on a CMC substrate.
摘要:
A coated substrate is provided that comprises: a substrate; and a barrier coating comprising a compound having the formula: Ln2ABOs, where Ln comprises scandium, yttrium, lanthanum, cerium, praseodymium, neodymium, promethium, samarium, europium, gadolinium, terbium, dysprosium, holmium, erbium, thulium, ytterbium, lutetium, or mixtures thereof; A comprises Si, Ti, Ge, Sn, Ce, Hf, Zr, or a combination thereof; and B comprises Mo, W, or a combination thereof. In one embodiment, B comprises Mo.
摘要:
A stacked up structure can include a first environmental barrier coating (EBC) layer and a second EBC layer. A first process can be used to form the first layer and a second process can be used to form the second layer. In one embodiment interfacial material can be formed for improved bonding of the second layer to the first layer. The interfacial material can define a continuous or discontinuous layer of nonuniform thickness.
摘要:
A rare earth silicate-based hermetic layer includes a thermal sprayed coating including a rare earth silicate having a hermetic microstructure. An environmental barrier coating includes a bond coat layer including silicon; and at least one rare earth silicate-based hermetic layer deposited on the bond coat layer by thermal spraying. The rare earth silicate-based hermetic layer includes a thermal sprayed coating including a rare earth silicate having a hermetic microstructure. An article for service in extreme environments may be provided with such an environmental barrier coating. A thermal spray feedstock for producing a rare earth silicate-based hermetic layer.
摘要:
A coated substrate is provided that includes an environmental barrier coating on (e.g., directly on) a surface of a substrate (e.g., a ceramic matrix composite). The environmental barrier coating can include a barrier layer having a refractory material phase and a silicon-containing glass phase. The silicon-containing glass phase may be a continuous phase within the barrier layer (e.g., a breathable grain boundary of the barrier layer), or may be a plurality of discontinuous layers dispersed throughout the refractory material phase. The refractory material phase can include a rare earth silicate material having a rare earth component at a first atomic percent, while the silicon-containing glass phase comprises the rare earth component at a second atomic percent that is less than the first atomic percent. Methods are also provided for forming a barrier layer on a substrate.
摘要:
A method of depositing abradable coating on an engine component is provided wherein the engine component is formed of ceramic matrix composite (CMC) and one or more layers, including at least one environmental barrier coating, may be disposed on the outer layer of the CMC. An outermost layer of the structure may further comprise a porous abradable layer that is disposed on the environmental barrier coating and provides a breakable structure which inhibits blade damage. The abradable layer may be gel-cast on the component and sintered or may be direct written by extrusion process and subsequently sintered.
摘要:
Methods and materials for forming in-situ features in a ceramic matrix composite component are described. The method of forming a ceramic matrix composite component with cooling features, comprises forming a preform tape, laying up said preform tape to a desired shape, placing a high-temperature resistant fugitive material insert of preselected geometry in the preform tape of the desired shape, compacting the preform tape of the desired shape, burning out the preform tape of the desired shape, melt infiltrating the desired shape, removing the high-temperature resistant insert to form the cooling features during one of the burning out or the melt infiltrating or following the burning out or the melt infiltrating.