| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | SINTERED BODY AND ELECTROSTATIC CHUCK | US15616857 | 2017-06-07 | US20170358476A1 | 2017-12-14 | Michio Horiuchi; Masakuni Miyazawa |
| A sintered body includes a ceramic substrate including sintered oxide particles, a through-hole formed in the ceramic substrate such that the side surfaces of the oxide particles exposed from an inner wall of the through-hole form a flat surface, and a porous body disposed in the through-hole, the porous body including spherical oxide ceramic particles and a mixed oxide configured to bind the spherical oxide ceramic particles. | ||||||
| 182 | COMPOSITE BODY AND METHOD FOR PRODUCING SAME | US15328723 | 2015-07-24 | US20170239715A1 | 2017-08-24 | Takeshi MIYAKAWA; Hideki HIROTSURU |
| A composite production method includes impregnating a plate-shaped porous inorganic structure and a fibrous inorganic material with a metal while the fibrous inorganic material is arranged to be adjacent to the porous inorganic structure. In the composite structure, first and second phases are adjacent to each other by using a porous inorganic structure having a porous silicon carbide ceramic sintered body and the fibrous inorganic material, the first phase being a phase in which the porous silicon carbide ceramic sintered body is impregnated with the metal, the second phase being a phase in which the fibrous inorganic material is impregnated with the metal, a percentage of the porous silicon carbide ceramic sintered body in the first phase is 50 to 80 volume percent, and a percentage of the fibrous inorganic material in the second phase is 3 to 20 volume percent. A composite is produced by the method. | ||||||
| 183 | Method of depositing abradable coatings under polymer gels | US15103261 | 2014-11-07 | US09714578B2 | 2017-07-25 | Glen Harold Kirby |
| 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. | ||||||
| 184 | SEGMENTED FLEXIBLE GEL COMPOSITES AND RIGID PANELS MANUFACTURED THEREFROM | US15367986 | 2016-12-02 | US20170081495A1 | 2017-03-23 | Owen R. Evans; Irene Melnikova |
| The present invention describes various methods for manufacturing gel composite sheets using segmented fiber or foam reinforcements and gel precursors. Additionally, rigid panels manufactured from the resulting gel composites are also described. The gel composites are relatively flexible enough to be wound and when unwound, can be stretched flat and made into rigid panels using adhesives. | ||||||
| 185 | SYSTEM FOR THERMALLY ISOLATING A TURBINE SHROUD | US14708336 | 2015-05-11 | US20160333713A1 | 2016-11-17 | Christopher Paul TURA; Dylan James Fitzpatrick |
| In one aspect the present subject matter is directed to a system for thermally isolating a turbine shroud of a turbine shroud assembly. The system includes a shroud support having an inner surface and a turbine shroud that is connected to the shroud support. The turbine shroud includes a hot side surface that is radially spaced from a back side surface. At least a portion of the back side surface is oriented towards the inner surface of the shroud support. The system further includes a coating that is disposed along the back side surface of the turbine shroud. The coating regulates heat transfer from the turbine shroud to the shroud support or other hardware that may surround or be adjacent to the turbine shroud. | ||||||
| 186 | SUBSTRATE WITH LOW-PERMEABILITY COATING FOR THE SOLIDIFICATION OF SILICON | US15022461 | 2014-09-12 | US20160222542A1 | 2016-08-04 | Jean-Paul GARANDET; Denis CAMEL; Béatrice DREVET; Nicolas EUSTATHOPOULOS; Charles HUGUET; Johann TESTARD; Rayisa VOYTOVYCH |
| A substrate characterised in that it is at least partially surface-coated with a coating containing at least one so-called “barrier” layer having silica and one or more material(s) X selected from among SiC, Si, Si3N4, in which layer the amount of X varies between 25-wt. % and 50.-wt. % in relation to the total weight of the barrier layer, the barrier layer being formed by grains of one or more materials X covered at least partially in a silica shell, and the barrier layer being in direct contact with the substrate. | ||||||
| 187 | Slurry-based coating restoration | US14213466 | 2014-03-14 | US09387512B2 | 2016-07-12 | Kang N. Lee; Adam Lee Chamberlain; Andrew Joseph Lazur |
| In some examples, a method includes identifying a damaged area in a ceramic matrix composite coating of an in-service component; applying a restoration slurry to the damaged area of the ceramic matrix composite coating, wherein the restoration slurry comprises a liquid carrier and a restoration coating material; drying the restoration slurry to form a dried restoration slurry; and heat treating the dried restoration slurry to form a restored portion of the ceramic matrix composite coating. In some examples, an assembly may include a component including a substrate and a coating on the substrate, where the coating defines a damaged portion; masking around the damaged portion on undamaged portions of the coating; and a restoration slurry in the damaged portion, wherein the restoration slurry comprises a liquid carrier and a restoration coating material. | ||||||
| 188 | BOND LAYER FOR SILICON-CONTAINING SUBSTRATES | US14947870 | 2015-11-20 | US20160145159A1 | 2016-05-26 | Sean E. Landwehr; Kang N. Lee; Adam Lee Chamberlain |
| In some examples, an article may include a substrate and a coating on the substrate. In accordance with some of these examples, the coating may include a bond layer and an overlying layer comprising at least one oxide. In some examples, the bond layer comprises silicon metal and at least one of a transition metal carbide, a transition metal boride, or a transition metal nitride. | ||||||
| 189 | Method of reinforcing irregular structures | US13696705 | 2011-05-10 | US09278889B2 | 2016-03-08 | Terrence John Rayner; David John Hastings; David Edward Livingstone |
| The present disclosure provides a method for reinforcing irregular rock or irregular concrete surfaces such as rock structures in mines as well as other rock and concrete structures. The method includes applying a curable foam composition to at least a portion of a surface, at least partially curing the curable foam composition to form a foam layer adhered to the surface, applying a curable reinforcing composition onto at least a portion of the foam layer, and at least partially curing the curable reinforcing composition to form a reinforcing layer, wherein at least a portion of the reinforcing layer is adhered to the foam layer. | ||||||
| 190 | VISUAL INDICATOR OF COATING THICKNESS | US14789676 | 2015-07-01 | US20160003092A1 | 2016-01-07 | Adam Lee Chamberlain; Andrew Joseph Lazur; Kang N. Lee |
| In some examples, a coating may include at least one feature that facilitates visual determination of a thickness of the coating. For example, the coating may include a plurality of microspheres disposed at a predetermined depth of the coating. The plurality of microspheres may define a distinct visual characteristic. By inspecting the coating and viewing at least one of the microspheres, the thickness of the coating may be estimated. In some examples, the plurality of microspheres may be embedded in a matrix material, and the distinct visual characteristic of the microspheres may be different than the visual characteristic of the matrix material. In other examples, the at least one feature may include at least one distinct layer in the coating system that includes a distinct visual characteristic, such as a color of the distinct layer. | ||||||
| 191 | PROTECTIVE COATING SYSTEMS FOR GAS TURBINE ENGINE APPLICATIONS AND METHODS FOR FABRICATING THE SAME | US14156502 | 2014-01-16 | US20150197456A1 | 2015-07-16 | Reza Oboodi; Eric Passman; Bahram Jadidian |
| Protective coating systems for gas turbine engine applications and methods for fabricating such protective coating systems are provided. An exemplary protective coating system includes a substrate formed of a ceramic matrix composite material, a first coating layer formed directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and a second coating layer formed directly on to the first coating layer and comprising a thermal barrier material. The exemplary protective coating optionally includes a third coating layer partially formed directly on to the second coating layer and partially formed within at least some of the plurality of pores of the second coating layer. | ||||||
| 192 | Dental application coating | US13378951 | 2010-06-17 | US09045378B2 | 2015-06-02 | Petrus Brännvall; Håkan Lindstrom; Erik Adolfsson |
| The invention relates to a dental application body, comprising an oxide ceramic, containing a bulk material containing an oxide ceramic, preferably a zirconium oxide, and at least one coating containing an yttrium oxide and/or cerium oxide stabilized zirconium oxide, wherein the content of the stabilizing compound (c[yttrium oxide], C[cerium oxide]) within the coating with respect to the zirconium oxide (in mol-%) satisfies the formula c[yttrium oxide]+0.6×c[cerium oxide]≧4. Furthermore, the invention relates to a method for producing such a dental application body comprising the steps of providing a bulk material containing an oxide ceramic, preferably a zirconium oxide having a tetragonal microstructure as a main phase, and applying at least one coating containing an yttrium oxide and/or cerium oxide stabilized zirconium oxide, wherein the content of the stabilizing compound (C[yttrium oxide], C[cerium oxide]) within the coating with respect to the zirconium oxide (in mol-%) satisfies the formula c[yttrium oxide]+0.6 ×c[cerium oxide]≧4. | ||||||
| 193 | HONEYCOMB STRUCTURE COMPRISING A MULTILAYER CEMENT SKIN | US13688891 | 2012-11-29 | US20140147621A1 | 2014-05-29 | Thomas Richard Chapman; Jacob George; Ralph Henry Hagg; Amit Halder; Huthavahana Kuchibhotla Sarma |
| Disclosed is a ceramic honeycomb structure comprising a honeycomb body and a multilayered outer layer formed of a thick core layer applied and rapidly dried and a thin clad layer dried more gently to form a crack free dual skin layer. The core layer may have properties that are closer to those of the ceramic honeycomb body in service than the clad layer that may provide a tough outer shell to withstand handling and assembly. | ||||||
| 194 | FEATURES FOR MITIGATING THERMAL OR MECHANICAL STRESS ON AN ENVIRONMENTAL BARRIER COATING | US13521647 | 2011-01-11 | US20130122259A1 | 2013-05-16 | Kang N. Lee |
| An article may include a substrate comprising a matrix material and a reinforcement material, a layer formed on the substrate, an array of features formed on the layer, and a coating formed on the layer and the array of features. The article may have improved thermal and/or mechanical stress tolerance compared to an article not including the array of features formed on the layer. | ||||||
| 195 | CORDIERITE-BASED COMPOSITE MEMBRANE COATED ON CORDIERITE MONOLITH | US13293745 | 2011-11-10 | US20130118355A1 | 2013-05-16 | Joel Edward Clinton; Yunfeng Gu |
| Composite-membrane monoliths include a cordierite monolith having a cordierite-ceramic composite membrane bonded to surfaces thereof with a surface median pore size. The cordierite-ceramic composite membrane has membrane surfaces with a membrane median pore size of 0.3 μm or less. The cordierite-ceramic composite membrane may be a composite formed by firing the cordierite monolith subsequent to applying a cordierite-ceramic composite slip to surfaces thereof. The cordierite-ceramic slip may include cordierite particles and ceramic particles. The cordierite particles may have a cordierite median particle size smaller than the surface median pore size. The ceramic particles may have a ceramic median particle size smaller than the cordierite median particle size. | ||||||
| 196 | METHOD OF REINFORCING IRREGULAR STRUCTURES | US13696705 | 2011-05-10 | US20130051918A1 | 2013-02-28 | Terrence John Rayner; David John Hastings; David Edward Livingstone |
| The present disclosure provides a method for reinforcing irregular rock or irregular concrete surfaces such as rock structures in mines as well as other rock and concrete structures. The method includes applying a curable foam composition to at least a portion of a surface, at least partially curing the curable foam composition to form a foam layer adhered to the surface, applying a curable reinforcing composition onto at least a portion of the foam layer, and at least partially curing the curable reinforcing composition to form a reinforcing layer, wherein at least a portion of the reinforcing layer is adhered to the foam layer. | ||||||
| 197 | METHODS FOR REPAIRING A TURBINE AIRFOIL CONSTRUCTED FROM CMC MATERIAL | US13188755 | 2011-07-22 | US20130022471A1 | 2013-01-24 | Herbert Chidsey Roberts, III; Paul Edward Gray; Roger Lee Ken Matsumoto; Jeffrey H. Boy; Philip Harold Monaghan; Joseph Halada |
| Methods for repairing a turbine airfoil constructed from a CMC material are provided via filling a cavity located in the turbine airfoil with a ceramic paste (e.g., including a ceramic powder and a binder), heating the ceramic paste in the cavity to remove the binder, thereby forming a porous ceramic material, and adding a molten ceramic material to the porous ceramic material. The cavity can be defined in an airfoil of the turbine airfoil (e.g., on a tip or cap of the airfoil). Intermediates formed during the repair of a turbine airfoil are also provided. The intermediate can generally include an airfoil comprising a CMC material, a cavity defined in the airfoil, and a porous ceramic material filling the cavity. | ||||||
| 198 | PREPARATION OF NANOSTRUCTURED MICROPOROUS COMPOSITE FOAMS | US13123614 | 2009-10-08 | US20120064243A1 | 2012-03-15 | Galip Akay; Burak Calkan; Hasan Hasni; Rozita Mohamed |
| A method of producing a monolithic metal or metal composite having a hierarchic pore structure, the method comprising the steps of: selecting a template material, said template material having a porous structure; contacting the template material with a solution of the or each metal to be structuralised; depositing the or each metal onto the template; washing the metal coated template before deposition of further metal; isolating the metal coated template material; removing, thermally, at least a portion of the template material. | ||||||
| 199 | SEPARATION MEMBRANE | US13170774 | 2011-06-28 | US20110253619A1 | 2011-10-20 | Masanobu AIZAWA |
| [Subject] The aim is to provide a separation membrane which can fulfill both high separation capability and high permeation rate.[Solving Means] The disclosed is separation membrane which comprises a porous substrate which is made of ceramic sintered body of which a main ingredient is alumina, and a zeolite membrane which is formed over the surface of the porous substrate, wherein the porous substrate comprises a base layer and a foundation layer which is formed on the base layer and is formed for the zeolite membrane, and the separation membrane is characterized in that a mean pore diameter of the foundation layer is smaller than a mean pore diameter of the base layer. | ||||||
| 200 | Method for preparing a porous inorganic coating on a porous support using certain pore fillers | US11880066 | 2007-07-19 | US07767256B2 | 2010-08-03 | Yunfeng Gu; Wei Liu; Jianguo Wang |
| Methods for preparing porous inorganic coatings on porous supports using certain pore fillers, and porous supports coated with porous inorganic coatings. The porous inorganic coatings may serve as membranes useful in, for example, liquid-liquid, liquid-particulate, gas-gas, or gas-particulate separation applications. | ||||||
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