56results about How to "Increased strain tolerance" patented technology

A configuration for coating a turbine component such as a blade or vane with various forms of thermal barrier coating to provide enhanced temperature capability and increased strain tolerance is disclosed. A gas path surface of the platform, airfoil and airfoil fillet region are first coated with a bond coating. A dense vertically cracked (DVC) thermal barrier coating is then applied to at least the gas path surface of the platform and can be applied to the fillet region. A porous thermal barrier coating is then applied to at least the airfoil. The porous thermal barrier coating can also be applied over the DVC thermal barrier coating if desired.

The invention relates to a multi-layer thermal barrier coating. The coating comprises a base body, a binding layer and a ceramic top layer which are sequentially arranged from bottom to top, wherein the ceramic top layer consists of a vertical-crack-containing ceramic bottom layer with different microstructures, a porous intermediate ceramic layer and a compact ceramic top layer, which are sequentially arranged from bottom to top; the invention further provides a forming method of the multi-layer thermal barrier coating; the forming method comprises the following steps: providing the base body and the binding layer; forming the vertical-crack-containing ceramic bottom layer on the upper surface of the binding layer by plasma spraying; forming the porous intermediate ceramic layer on the upper surface of the vertical-crack-containing ceramic bottom layer by virtue of plasma spraying; forming the compact ceramic top layer on the upper surface of the porous intermediate ceramic layer by virtue of plasma spraying. The multi-layer thermal barrier coating containing different microstructures is formed by the vertical-crack-containing ceramic bottom layer, the porous intermediate ceramic layer and the compact ceramic top layer which are sequentially arranged from bottom to top, so that the multi-layer thermal barrier coating has a thermal cycle service life which multiple times that of the existing thermal barrier coating.

A composition comprising a glass-forming binder component and a particulate corrosion resistant component. The particulate corrosion resistant component comprises corrosion resistant particulates having: a CTE_p of at least about 4 and being solid at a temperature of about 1300° F. (704° C.) or greater; and a maximum median particle size defined by one of the following formulas: (a) for a CTE_p of 8 or less, an M_p equal to or less than (4.375×CTE_p)−10; and (b) for a CTEp of greater than 8, an M_p equal to or less than (−4.375×CTE_p)+60, wherein CTE_p is the average CTE of the corrosion resistant particulates and wherein M_p is the median equivalent spherical diameter (ESD), in microns, of the corrosion resistant particulates. Also disclosed is an article comprising a turbine component comprising a metal substrate and a corrosion resistant coating overlaying the metal substrate, as well as a method for forming at least one layer of the corrosion resistant coating adjacent to the metal substrate. The corrosion resistant coating has a maximum thickness defined by one of the following formulas: (3) for a CTE_p of 8 or less, an T_c equal to or less than (1.5×CTE_p)−3.5; and (4) for a CTE_p of greater than 8, an T_c equal to or less than (−1.5×CTE_p)+20.5, wherein T_c is the thickness, in mils, of the corrosion resistant coating.

The invention relates to an automatic preparation method of a long-service-life cylinder-like crystal structural thermal barrier coating on the surface of a guide blade of a hot end part of a fuel machine. According to the invention, a supersonic flame spray gun and a plasma spray gun are respectively clamped by manipulators; an automatic spraying program is compiled; for a supersonic flame spraying bonding layer, by a main program, a distance from a TCP (Transmission Control Protocol) point to a spray gun orifice is set into 330 to 350mm, a moving speed of the spray gun is set into 500 to 600m/s and a spacing of spraying profiles is set into 20 to 30mm; for a plasma spraying ceramic layer, by the main program, a distance from the TCP point to a spray gun orifice is set into 60 to 70mm, a moving speed of the spray gun is set into 200 to 250m/s, a spacing of spraying profiles is set into 3 to 7mm; in the plasma spraying program compiling process, the trend of each spraying profile is of a shape of a Chinese character 'gong'. The automatic preparation method sequentially comprises the steps of preparation and pretreatment of a matrix, preparation of a bonding layer, preheating of the hot end part and preparation of a ceramic layer; a scanning electron microscope is adopted to observe; the prepared ceramic layer is of a cylinder-like crystal structure; strain tolerance and the thermal shock resistance service life of the coating are obviously improved; compared with the service life of the conventional structural thermal barrier coating, the service life of the coating is obviously prolonged.

The invention discloses a preparation technology of an anti-sintering dual-die composite structure thermal barrier coating. The preparation technology includes the steps that first, metal is depositedon a substrate to form a metal bonding layer; second, first thermal barrier coating material powder and second thermal barrier coating material powder are deposited on the metal bonding layer in an alternative layered mode through a thermal spraying method to form a composite layered structure thermal barrier coating; and third, a plurality of longitudinal holes are formed in the composite layered structure thermal barrier coating through a strong flow impingement cooling pretreatment technology, and accordingly the dual-die composite structure thermal barrier coating can be obtained. According to the dual-die composite structure provided by the invention, the multiple holes perpendicular to the heat flow direction are spontaneously formed on service, high-strain tolerance is maintained and thus the characteristics of being resistant to sintering and long in service life are achieved.

The invention discloses an Yb modified CMAS prevention composite structure thermal barrier coating and a preparing method thereof. A CMAS corrosion prevention layer adopts Yb modified rare earth zirconate to form a compact layered structure, at the high temperature, the layered structure can have a reaction with CMAS to form a compact blocking layer, permeation of molten CMAS to the interior of the thermal barrier coating can be prevented, a first heat insulation layer adopts Yb modified rare earth zirconate to form a columnar structure, enough heat insulation performance and high strain tolerance can be provided for the thermal barrier coating, the thermal shock property of the thermal barrier coating is improved, the service life of the thermal barrier coating can be prolonged, the CMAScorrosion prevention layer and the first heat insulation layer are made of materials of the same elements, heat mis-match stress between the two layers can be relieved, combining strength of the two layers can be improved, the thermal barrier coating has the advantages of being low in heat conduction rate, stable in phase, high in combining strength, and high in sintering resisting capacity, the service life under the high-temperature service condition is long, combination strength between dual layers of ceramic can be high, and combination strength between a ceramic layer and a metal bondinglayer is high.

The invention relates to a coating and a preparing method thereof, in particular to a coating improving oxidation resistance of TiAl alloy and a preparing method of the coating. The coating improving oxidation resistance of TiAl alloy comprises an AlSiY bottom layer and a YSZ ceramic face layer, the AlSiY bottom layer is prepared through vacuum arc plating, and high-temperature diffusion and wet grit blasting treatment is carried out. The YSZ ceramic face layer of a columnar crystal structure is prepared through an electron beam physical vapor deposition method, and a typical columnar crystal structure is presented. The interfacial compatibility of the coating improving oxidation resistance of TiAl alloy and TiAl alloy is good, the oxidation resistance is superior, and the strain tolerance is high.

The invention discloses an anti-sintering dual-mode complex structure thermal barrier coating layer and a preparation process thereof. The preparation process comprises the following steps: Step I, depositing a metal on a matrix to form a metal adhesive layer; Step II, alternating layering and depositing thermal barrier coating layer powder and phase-change shrinkable ceramic material powder on the metal adhesive layer to form a composite lamellar structure thermal barrier coating layer; Step III, forming a plurality of longitudinal pores in the composite lamellar structure thermal barrier coating layer through strong flow impact cooling pretreatment process to obtain a dual-mode complex structure thermal barrier coating layer; Step IV, generating phase-change shrinkage through a second lamella unit in a thermal treatment or actual application process of the dual-mode complex structure thermal barrier coating layer and the matrix, so as to obtain the anti-sintering dual-mode complex structure thermal barrier coating layer. The structure of the anti-sintering dual-mode complex structure thermal barrier coating layer spontaneously forms a plurality of pores perpendicular to a heat flow direction when serving in a high temperature environment, maintains a high strain tolerance and has the characteristics of sintering resistance and long service life.

The invention relates to a ceramic-based annular flame tube. The ceramic-based annular flame tube comprises a tube main body, a rear support and a front end cover, wherein the tube main body and the rear support are made of integrally-woven SiCf/SiCm materials, and the front end cover is made of high-temperature alloy. According to the ceramic-based annular flame tube, ellipse-like inclined holesare designed to be formed in the tube wall of the flame tube, and the circumferential inclination angle is set to achieve the optimal cooling effect; in order to solve the problem of thermal mismatchof connection between parts made of different materials, thermal mismatch compensation slits are formed in a head joint and the rear support; and the flame tube made of a ceramic matrix composite is mainly applied to aero-engines and has the characteristics of being light in weight, high in using temperature, good in cooling effect, convenient to machine and the like.

The invention relates to the field of high-temperature functional ceramic coating materials, and particularly discloses a thickness-adjustable thermal insulation/infrared stealth composite coating. The composite coating is of a multi-layer stacked structure and sequentially comprises a metal bonding layer, a ceramic layer and an infrared low-emissivity layer from inside to outside, the ceramic layer is a lanthanum phosphate-hexaaluminate composite ceramic layer, and the infrared low-emissivity layer is a low-emissivity coating which is formed by taking Bi2O3-Al2O3-TiO2-Li2O-SiO2 series low-melting-point glass as a binding phase and taking silver as a conductive phase. A titanium alloy material with the surface coated with the coating and a preparation method of the titanium alloy materialare further provided. The heat insulation/infrared stealth composite coating has the characteristics of excellent thermal shock resistance and high-temperature infrared low emissivity; and the thickness of the coating can be regulated and controlled according to different actual application requirements, and the density and the heat insulation performance of the coating surface can be regulated.

The invention discloses an anti-sintering long-service-life gradient column layer composite structure thermal barrier coating and a preparation method thereof. The coating is divided by longitudinal gaps and formed by superposing N sub-layers and is of a gradient column layer composite structure. The ratios of the thicknesses of all sub-layers to the thermal conductivity are the same. The thermalconductivity of the sub-layers is decreased progressively by the equal difference from the first sub-layer close to a bonding layer to the N sub-layer. Each sub-layer is formed by depositing firstthermal barrier coating material powder and second thermal barrier coating material powder in an alternately-layering manner. The formation compactness of the first thermal barrier coating material powder is greater than that of 90% of slice layer units. The formation compactness of the second thermal barrier coating material powder is less than that of 60% of the slice layer units. The volume ofa second thermal barrier coating material accounts for 10-50% of the total volume of the thermal barrier coating. By means of the anti-sintering long-service-life gradient column layer composite structure thermal barrier coating and the preparation method thereof, the purpose that the ceramic coating resists to sintering in a high-temperature environment is achieved; by means of the gradient columnar structure design, the reverse restriction relation of a singular structure coating for the thermal insulation capability and the service life is broken through; and collaborative design of sintering resistance and the long service life is guaranteed.

The invention discloses a CrAlN thermal insulation coating for an aluminum alloy piston combustor surface and a preparation method thereof. The CrAlN thermal insulation coating comprises a transitionlayer and a thermal insulation layer from the inside out in order, the transition layer is a CrAl coating, and the thermal insulation layer is a CrAlN coating. The method adopts filtered cathodic vacuum arc technique, takes a CrAl alloy target material (Cr, Al metal target) as the cathode, performs deposition of the CrAl coating on the aluminum alloy surface to form a transition layer, then uses nitrogen as the working gas, and coats the transition layer surface with the CrAlN coating evenly to form the thermal insulation layer. The CrAlN thermal insulation coating provided by the invention not only solves the problem of poor binding force and bearing ability caused by large difference of basic physical properties between the CrAlN coating and the aluminum alloy substrate material, also the coating is uniform and compact, has good film-substrate combination state and hardness up to 40GPa, and shows good high temperature thermal insulation properties and thermal shock resistance in piston thermal load test. The CrAlN thermal insulation coating provided by the invention significantly improves the performance reliability and service life of the aluminum alloy piston, and can meet thehigh power and low emission development requirements of modern engines.

The invention relates to a preparation method of a DVC thermal barrier coating, which comprises the following steps: providing powder, the chemical components of which are YSZ or YSZ + xGd2O3 + yYb2O3 or Gd2Zr2O7 + zYb2O3 or LaMgAl11O19 or La2 (Zr0. 7Ce0. 3) 2O7, x + y is less than or equal to 12wt%, z is less than or equal to 20wt%; the powder forms the DVC thermal barrier coating through high-heat-enthalpy atmosphere plasma spraying. The invention further provides the DVC thermal barrier coating obtained through the preparation method. The invention further provides application of the DVC thermal barrier coating. The DVC thermal barrier coating is used for a high-temperature hot end component of an aero-engine or a gas turbine. The chemical components of the DVC thermal barrier coating are YSZ or YSZ + xGd2O3 + yYb2O3 or Gd2Zr2O7 + zYb2O3 or LaMgAl11O19 or La2 (Zr0. 7Ce0. 3) 2O7, the applicable material range is wide, the strain tolerance can be increased, the working temperature can be increased, the erosion and erosion resistance can be improved, and the thermal shock resistance cycle life can be prolonged.

The invention discloses an anti-thermal-shock thermal barrier coating with low thermal conductivity. Compared with a traditional thermal barrier coating, carbon powder is added, after high temperature calcination modification is conducted, the porosity rate of a ceramic phase can be increased, and the thermal insulating performance of the coating can be significantly improved. In addition, by means of a modification method, Zr<4+> is replaced with Y<3+> and Ce<4+> in zirconium dioxide crystal lattices, oxygen vacancies and local stress fields are produced, the phonon scattering in the crystal lattices is increased, and the thermal conductivity is significantly decreased; the atomic mass of solid solution atoms Ce is far larger than that of Y, the scattering intensity of phonons in the anti-thermal-shock thermal barrier coating can be significantly improved, and therefore the thermal conductivity is decreased. According to the anti-thermal-shock thermal barrier coating with the low thermal conductivity and a preparation method thereof, the preparation technology is simple, the prepared coating is high in surface hardness, low in water absorption, good in toughness, not prone to cracking and layering, high in strain tolerance and long in anti-thermal-shock life, and the service life of the anti-thermal-shock thermal barrier coating with the low thermal conductivity is significantly prolonged compared with a thermal barrier coating of a conventional structure.

A cabled conductor comprises a plurality of transposed strands each comprising one or more preferably twisted filaments preferably surrounded or supported by a matrix material and comprising textured anisotropic superconducting compounds which have crystallographic grain alignment that is substantially unidirectional and independent of the rotational orientation of the strands and filaments in the cabled conductors. The cabled conductor is made by forming a plurality of suitable composite strands, forming a cabled intermediate from the strands by transposing them about the longitudinal axis of the conductor at a preselected strand lay pitch, and, texturing the strands in one or more steps including at least one step involving application of a texturing process with a primary component directed orthogonal to the widest longitudinal cross-section of the cabled intermediate, at least one such orthogonal texturing step occurring subsequent to said strand transposition step. In a preferred embodiment, the filament cross-section, filament twist pitch, and strand lay pitch are cooperatively selected to provide a filament transposition area which is always at least ten times the preferred direction area of a typical grain of the desired anisotropic superconducting compound. For materials requiring biaxial texture, the texturing step preferably includes application of a texturing process with a second primary component in a predetermined direction in the plane of the widest longitudinal cross-section of the conductor.