1830 results about "Thermal barrier coating" patented technology

Components (1) have a thermal barrier coating (2-6) on the surface thereof, wherein the thermal barrier coating includes at least one layer (3) having chemically stabilized zirconia, and wherein at least indirectly adjacent to the layer (3) with chemically stabilized zirconia and on its surface facing side, there is provided a protective layer (4) and/or a infiltration zone (5) which does not react with environmental contaminant compositions that contain oxides of calcium and which does not react with the material of the layer (3) having chemically stabilized zirconia. Methods for making such components as well as to uses of specific systems for coating thermal barrier coatings, can prevent CMAS.

A ceramic thermal barrier coating (TBC) (18) having first and second layers (20, 22), the second layer (22) having a lower thermal conductivity than the first layer for a given density. The second layer may be formed of a material with anisotropic crystal lattice structure. Voids (24) in at least the first layer (20) make the first layer less dense than the second layer. Grooves (28) are formed in the TBC (18) for thermal strain relief. The grooves may align with fluid streamlines over the TBC. Multiple layers (84, 86,88) may have respective sets of grooves (90), Preferred failure planes parallel to the coating surface (30) may be formed at different depths (A1, A2, A3) in the thickness of the TBC to stimulate generation of a fresh surface when a portion of the coating fails by spalling. A dense top layer (92) may provide environmental and erosion resistance.

Improved environmental barrier coatings and improved organic semiconductor devices employing the improved environmental barrier coatings are disclosed herein. Methods of making and using the improved coatings and devices are also described. An improved environmental barrier coating generally includes a primary barrier layer, a secondary barrier layer disposed on the primary barrier layer, and a passivation layer disposed on the secondary barrier layer. The secondary barrier layer is formed using atomic layer deposition.

A device having an improved thermal barrier coating (46) and a process for manufacturing the same. A support structure (28) for retaining a ceramic insulating material (46) on a substrate (16) is formed by the deposition of a support structure material through a patterned masking material (14). The support structure can define cells into which the ceramic insulating material is deposited following removal of the masking material. The masking material may be patterned by known photolithographic techniques (22,24) or by laser etching (48). The support structure (28) may be a composite metal-ceramic material having either discreet layers (30,34) or a graded composition and may be deposited by an electro-desposition process followed by a heat treatment to form a solid state diffusion bond with the substrate. The ceramic filler material may be deposited (44) by the electrophoretic deposition of ceramic particles coated with a bonding material that is subsequently heated to oxidize and to bond the particles together. The support structure may be provided with included walls in order to improve its resistance to foreign object impact damage.

A coating applied as a two layer system. The outer layer is an oxide of a group IV metal selected from the group consisting of zirconium oxide, hafnium oxide and combinations thereof, which are doped with an effective amount of a lanthanum series oxide. These metal oxides doped with a lanthanum series addition comprises a high weight percentage of the outer coating. As used herein, lanthanum series means an element selected from the group consisting of lanthanum (La), cerium (Ce), praseodymium (Pr), neodymium (Nd), promethium (Pm), samarium (Sm), europium (Eu), gadolinium (Gd), terbium (Tb), dysprosium (Dy), holmium (Ho), erbium (Er), thulium (Tm), ytterbium (Yb), lutetium (Lu) and combinations thereof, and lanthanum series oxides are oxides of these elements. When the zirconium oxide is doped with an effective amount of a lanthanum series oxide, a dense reaction layer is formed at the interface of the outer layer of TBC and the CMAS. This dense reaction layer prevents CMAS infiltration below it. The second layer, or inner layer underlying the outer layer, comprises a layer of partially stabilized zirconium oxide.

A method for applying a plasma prayed coating using liquid injection is disclosed. The method includes providing a mixture of a liquid and solid particles. The solid particles are constituents of a thermal barrier coating. The mixture is injected into a plasma jet of a plasma spray device and the plasma jet is directed toward a substrate to deposit a gradient film formed from the constituents onto the substrate.

A method of remotely monitoring the radiant energy (6) emitted from a turbine component such as a turbine blade (1) having a low-reflective surface coating (3) which may be undergoing potential degradation is used to determine whether erosion, spallation, delamination, or the like, of the coating (3) is occurring.

A coating material for a component intended for use in a hostile thermal environment. The coating material has a cubic microstructure and consists essentially of either zirconia stabilized by dysprosia, erbia, gadolinium oxide, neodymia, samarium oxide or ytterbia, or hafnia stabilized by dysprosia, gadolinium oxide, samarium oxide, yttria or ytterbia. Up to five weight percent yttria may be added to the coating material.

A coating system for Si-containing materials, particularly those for articles exposed to high temperatures. The coating system exhibits improved resistance to corrosion from sea salt and CMAS as a result of using aluminate compounds to protect silicate-containing layers of the coating system. The coating system includes an environmental barrier coating, a thermal barrier coating overlying the environmental barrier coating and formed of a thermal-insulating material, and a transition layer between the environmental barrier coating and thermal barrier coating, wherein the transition layer contains at least one aluminate compound and/or alumina.

A multilayered ceramic topcoat of a thermal barrier coating system is useful for high temperature corrosive applications such as hot section components in gas turbine engines. The ceramic topcoat includes at least two layers, each having generally columnar grain microstructures with different grain orientation directions. A preferred method of producing the multilayered ceramic topcoat includes positioning a superalloy substrate at a first angled orientation relative to a ceramic vapor cloud in an electron beam physical vapor deposition apparatus for a time sufficient to grow a first ceramic layer. The substrate is then reoriented to a second, different angled orientation for a time sufficient to grow a second ceramic layer. The ceramic layers exhibit columnar microstructures having respective grain orientation directions which are related to the first and second substrate orientations. For uniformly coating a complex contoured surface such as a turbine blade airfoil, the blade can be rotated during coating deposition at each angled orientation. Alternatively, the article may be continuously reoriented according to a predetermined speed cycle to produce generally arcuate, sinusoidal, helical, or other columnar grain microstructures.

A ceramic material has particular utility as a thermal insulating or thermal barrier coating on metallic substrates. The ceramic material includes gadolinia and hafnia, preferably forming gadolinia-hafnia. This material exhibits chemical stability, thermal stability and thermal insulating properties superior to those of currently used thermal barrier ceramics, and also provides resistance to sintering and erosion comparable to currently used ceramics. A preferred material has between about 3-70 mol. % hafnia, balance hafnia.

An improved slurry formulation for the production of a thermal and environmental barrier coatings are provided which can withstand high temperature applications. The slurry includes a combination of a coarse ceramic powder fraction having close porosity particles and a fine ceramic powder fraction. The combination of the two powders produces a bimodal particle size distribution having a controlled amount of closed porosity that imparts desirable properties to the coating produced. The finer solid particles are interdispersed within an aqueous binder to produce a ceramic matrix with sufficient mechanical strength. The closed porosity containing coarse particles are embedded within the resultant ceramic matrix and do not disintegrate under high temperature conditions to impart a temperature resistant, non-collapsing closed porosity to the coating which can also act as an environmental barrier.

A protective barrier coating system including a diffusion barrier coating and an oxidation barrier coating and method for use in protecting silicon-based ceramic turbine engine components. A complete barrier coating system includes a thermal barrier coating of stabilized zirconia and an environmental barrier coating of an alloyed tantalum oxide. The oxidation barrier coating includes a layer of metallic silicates formed on a substrate of silicon nitride or silicon carbide to be protected. The oxidation barrier coating can include silicates of scandium, ytterbia or yttrium. The oxidation barrier coating may also include an inner layer of Si₂ON₂ between the diffusion barrier and the metallic silicate layer. The oxidation barrier coating can be applied to the substrate by spraying, slurry dipping and sintering, by a sol-gel process followed by sintering, by plasma spray, or by electron beam-physical vapor deposition. The diffusion layer of essentially pure Si₃N₄ can be applied to the substrate to prevent the migration of damaging cations from the protective layers to the substrate and is preferably formed by chemical vapor deposition. A method for protecting silicon based substrates can comprise a step of forming an oxidation barrier coating on a substrate, where a step of forming the oxidation barrier includes a step of sintering the oxidation barrier and substrate in a wet gas containing hydrogen.

The invention provides a multilayer thermal barrier coating and a preparation method thereof. The multilayer thermal barrier coating sequentially comprises an adhesion layer, a first ceramic layer, a second ceramic layer and a closing layer from bottom to top, wherein the closing layer has the thickness of 10-30 micros and the porosity of 2-8 percent and is made from the Al2O3. The thermal barrier coating can be prepared by adopting an electron beam physical gas-phase deposition technology or a plasma spraying method. The multilayer thermal barrier coating provided by the invention can avoid the stripping of the ceramic layers in a thermal circulating process, the thermal erosion resistance of the thermal barrier coating is greatly improved than the dual ceramic layers; and vertical crackles are introduced in the ceramic layer through improving a conventional plasma spraying process so that the thermal shock life of the thermal barrier coating is greatly prolonged.

Exemplary embodiments provide methods and systems for assembling electronic devices, such as integrated circuit (IC) chips, by selectively and scalably embedding or seating IC elements onto/into a receiving substrate, such as a chip substrate. Preparing of the chip substrate can be performed by depositing or patterning an activatable thermal barrier material on a surface of the substrate. The IC chips are secured on the prepared substrate by activating the thermal barrier material between the chip substrate and IC chips. Securing can include softening of the chip substrate with the activated thermal barrier material to an amount suitable for embedding the IC chips. Securing can also include adhesively bonding the IC chips to the substrate with the activated thermal barrier material in the case of a non-pliable substrate.

A catalyst element (30) for high temperature applications such as a gas turbine engine. The catalyst element includes a metal substrate such as a tube (32) having a layer of ceramic thermal barrier coating material (34) disposed on the substrate for thermally insulating the metal substrate from a high temperature fuel/air mixture. The ceramic thermal barrier coating material is formed of a crystal structure populated with base elements but with selected sites of the crystal structure being populated by substitute ions selected to allow the ceramic thermal barrier coating material to catalytically react the fuel-air mixture at a higher rate than would the base compound without the ionic substitutions. Precious metal crystallites may be disposed within the crystal structure to allow the ceramic thermal barrier coating material to catalytically react the fuel-air mixture at a lower light-off temperature than would the ceramic thermal barrier coating material without the precious metal crystallites.

Methods and apparatus for depositing thermal barrier coatings on gas turbine blades and vanes using Electron Beam Physical Vapor Deposition (EBPVD) combined with Ion Beam Assisted Deposition (IBAD).

A system for producing at least one trench to improve film cooling in a sample is provided. The system includes at least one laser source outputting at least one pulsed laser beam. The pulsed laser beam includes a pulse duration including a range less than about 50 μs, an energy per pulse having a range less than about 0.1 Joule, and a repetition rate with a range greater than about 1000 Hz. The system also includes a control subsystem coupled to the laser source, the control subsystem configured to synchronize a position of the sample with the pulse duration and energy level in order to selectively remove at least one of a thermal barrier coating, a bondcoat and a substrate metal in the sample to form the at least one trench.

Thermal barrier coated RF radomes and a method for making the same are provided. In an embodiment of the disclosure, there is provided a method for making a thermal barrier coated radio frequency (RF) radome. The method comprises providing a radio frequency (RF) radome. The method further comprises applying a thermal barrier coating having a dielectric constant less than about 2.0 onto a surface of the radome to form a thermal barrier coated RF radome. The thermal barrier coating reduces a structure temperature of the radome by greater than 300 degrees Fahrenheit to enhance thermo-mechanical properties and performance of the RF radome.

A turbine engine component comprising a substrate made of a nickel-base or cobalt-base superalloy, a non-metallic oxide or nitride diffusion barrier layer overlying the substrate, and a protective coating overlying the barrier layer, the protective coating comprising at least one platinum group metal selected from the group consisting of platinum, palladium, rhodium, ruthenium and iridium. The diffusion barrier layer may be a deposited or thermally grown oxide material, especially aluminum oxide. The protective coating may be heat treated to increase homogeneity of the coating and adherence with the substrate. The component typically further comprises a ceramic thermal barrier coating overlying the protective coating. Also disclosed are methods for forming a protective coating system on the turbine engine component by forming the non-metallic oxide or nitride diffusion barrier layer on the substrate and then depositing the platinum group metal on top of the barrier layer.