| Patent application number | Description | Published |
|---|
| 20080199661 | Thermally insulated CMC structure with internal cooling - An insulated CMC structure ( | 08-21-2008 |
| 20080206542 | Ceramic matrix composite abradable via reduction of surface area - A ceramic matrix composite with an enhanced abradability has a patterned surface with an array of solid composite material and voids where the voids extend into but not through the composite. The flow of gas through the voids as the surface is traversed by an impinging component, such as a turbine blade tip, is inhibited by the shape and size of the voids which can be sealed by the passing blade tip. Separately or additionally the inhibition of gas flow can result from the filling of the voids with a ceramic material of higher abradability than the ceramic matrix composite. | 08-28-2008 |
| 20080207075 | Optimized fabric lay-up for improved ceramic matrix composites - A ceramic matrix composite (CMC) is constructed from ceramic fabric sheets and a ceramic matrix to yield matrix rich zone of reduced dimensions between fabric sheets. This reduction in dimension decreases the occurrence of delamination between the fabric sheets. The fabric is optimized to reduce the size of matrix rich zones in the composite by increasing the number of fabric plies in a given thickness of composite. | 08-28-2008 |
| 20080274336 | High temperature insulation with enhanced abradability - A enhanced abradable friable graded insulator FGI results from the laser patterning of a coating where a series of top surfaces reside on a series of columns such that the walls of the columns are not significantly densified relative to the interior of the columns. Patterns can be generated where the columns are oriented independently normal to or at an acute angle to the top surfaces. The cross sections of the top surfaces are formed to conform to the average dimensions of the spheres of the FGI coating. The cross sections of the top surfaces can be more than 1.5 times the diameter of the spheres. Various patterns of top surfaces can be used including regular, random, quasiperiodic patterns. A gradient of abradability can be imposed on the coating. | 11-06-2008 |
| 20080279678 | Abradable CMC stacked laminate ring segment for a gas turbine - A pattern of depressions ( | 11-13-2008 |
| 20080280101 | Patterned reduction of surface area for abradability - A gas turbine component ( | 11-13-2008 |
| 20080284059 | Process for applying a thermal barrier coating to a ceramic matrix composite - A method of bonding an insulation layer ( | 11-20-2008 |
| 20090081033 | Stacked Lamellae Ceramic Gas Turbine Ring Segment Component - A gas turbine ring segment ( | 03-26-2009 |
| 20100019412 | METHOD OF MANUFACTURING A THERMAL INSULATION ARTICLE - A method of manufacturing a thermal insulation article may include positioning, between opposing mold walls, a first layer comprising a ceramic matrix composite (CMC) material and a second layer comprising a plurality of tiles. The method may further include moving the opposing mold walls together to compress together the first and second layers, and curing the compressed together first and second layers to produce the thermal insulation article. | 01-28-2010 |
| 20100021643 | Method of Forming a Turbine Engine Component Having a Vapor Resistant Layer - A method of forming a turbine component that includes a ceramic matrix composite-ceramic insulation composite with a vapor resistant layer is disclosed. The method includes providing an inner tool and an outer tool, wherein the inner and outer tools define a mold for forming a turbine component. A vapor resistant layer can be applied to the inner tool, and a ceramic insulation layer can be applied over the vapor resistant layer in the mold. The vapor resistant layer and the ceramic insulation layer can be partially fired to form a bisque turbine component, and the outer tool can be removed. The inner tool can include a transitory material. A layer of ceramic matrix composite material can be applied to the outside of the bisque turbine component to form a component, and the component can be fired to form a turbine component. | 01-28-2010 |
| 20100021713 | STRUCTURE AND METHOD FOR PROTECTING A HYBRID CERAMIC STRUCTURE FROM MOISTURE ATTACK IN A HIGH TEMPERATURE ENVIRONMENT - A hybrid ceramic structure and a method for protecting the hybrid ceramic structure from moisture attack in a high temperature combustion environment are provided. The structure includes a ceramic matrix composite (CMC) substrate ( | 01-28-2010 |
| 20100032875 | Processing method for solid core ceramic matrix composite airfoil - A method of processing solid core ceramic matrix composite articles. The method improves the physical characteristics of the article by forming the airfoil using a co-processing method wherein a refractory ceramic is cast against a preformed ceramic matrix composite (CMC) shell. In one aspect, the shell is continuous to help prevent delaminations. In another aspect, the shell is open. In one embodiment, the article includes a split line. The split line helps the article to be less susceptible to damage caused from internal strain. | 02-11-2010 |
| 20100047512 | METHODOLOGY AND TOOLING ARRANGEMENTS FOR STRENGTHENING A SURFACE BOND IN A HYBRID CERAMIC MATRIX COMPOSITE STRUCTURE - A ceramic matrix composite (CMC) structure and methods of fabricating such structure are disclosed. In one example, the surface of a CMC substrate ( | 02-25-2010 |
| 20100047526 | SUBSURFACE INCLUSIONS OF SPHEROIDS AND METHODOLOGY FOR STRENGTHENING A SURFACE BOND IN A HYBRID CERAMIC MATRIX COMPOSITE STRUCTURE - Structural arrangements and methodology are provided for strengthening a bond between corresponding surfaces of a thermally insulating ceramic coating ( | 02-25-2010 |
| 20100074726 | GAS TURBINE AIRFOIL - A gas turbine airfoil ( | 03-25-2010 |
| 20100074729 | Compressible Ceramic Seal - A stack of substantially parallel ceramic plates ( | 03-25-2010 |
| 20100075106 | SUBSURFACE INCLUSION OF FUGITIVE OBJECTS AND METHODOLOGY FOR STRENGTHENING A SURFACE BOND IN A HYBRID CERAMIC MATRIX COMPOSITE STRUCTURE - A hybrid ceramic matrix composite (CMC) structure | 03-25-2010 |
| 20100080953 | Formation of Imprints and Methodology for Strengthening a Surface Bond in a Hybrid Ceramic Matrix Composite Structure - A hybrid ceramic matrix composite structure and method for fabricating such an structure are provided. A ceramic matrix composite substrate | 04-01-2010 |
| 20100119777 | Ceramic matrix composite surfaces with open features for improved bonding to coatings - A method to form an improved hybrid ceramic matrix composite structure comprises providing a ceramic matrix composite (CMC) with open features at a surface and applying a thermal barrier coating to the surface. The thermal barrier coating is preferably a friable graded insulation coating (FGI) having hollow ceramic spheres. For acceptance of a FGI coating the open features have a center-to-center separation distance in one or more directions that is between about 100 and about 1,000 percent of the diameter of the hollow ceramic spheres in the FGI and a depth that is between about 20 percent and about 200 percent of the diameter of the hollow ceramic spheres in the FGI. The open feature can result from the winding of tows about a mandrel; the lay-up of fabric including a surface fabric having an open weave; or the use of a 3-D weave, or a 3-D braid. | 05-13-2010 |
| 20100221485 | THREE DIMENSIONAL REINFORCED CMC ARTICLES BY INTERLOCKING TWO DIMENSIONAL STRUCTURES - The interlocking of two or more sections via the insertion of one or more out-of-plane features in one section or combination of sections through a void in one or more a complementary sections can result in a reinforced ceramic matrix composite article upon securing of the sections. The sections can be secured by friction between two tightly matched sections or by the use of a pin, hook, or clamp. The sections can be constructed from one or more CMC laminate sheets. The out-of-plane feature can be a loop or a flange and the void can be an orifice or a matched loop in the complementary sheet. The securing of the sections can result in a CMC article where the delamination between sheets is inhibited. | 09-02-2010 |
| 20100251721 | Stacked laminate gas turbine component - A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material. | 10-07-2010 |
| 20100279072 | Gussets for Strengthening CMC Fillet Radii - A ceramic matrix composite (CMC) structure ( | 11-04-2010 |
| 20100291348 | Methodology and Tooling Arrangements for Increasing Interlaminar Shear Strength in a Ceramic Matrix Composite Structure - Methodology and tooling arrangements for increasing interlaminar shear strength in a ceramic matrix composite (CMC) structure are provided. The CMC structure may be formed by a plurality of layers of ceramic fibers disposed between a top surface and a bottom surface of the composite structure. A plurality of surface recesses are formed on the surfaces of the structure. For example, each of the surfaces of the composite structure may be urged against corresponding top and bottom surfaces of a tool having a plurality of asperities. The plurality of surface recesses causes an out-of-plane sub-surface fiber displacement along an entire thickness of the structure, and the sub-surface fiber displacement is arranged to increase an interlaminar shear strength of the structure. | 11-18-2010 |
| 20100291349 | Subsurface Inclusions of Objects for Increasing Interlaminar Shear Strength of a Ceramic Matrix Composite Structure - A ceramic matrix composite (CMC) structure | 11-18-2010 |
| 20110008154 | Sealing Arrangement for Turbine Engine Having Ceramic Components - A sealing arrangement for use in a turbine engine having ceramic components. The sealing arrangement is retained in a seal gap formed between adjacent segments and is compliant to accommodate variations in the size of the seal gap as the adjacent segments move relative to one another. | 01-13-2011 |
| 20110132562 | WAXLESS PRECISION CASTING PROCESS - Alloy products are produced with a waxless casting process. A model of a ceramic casting vessel ( | 06-09-2011 |
| 20110132563 | INVESTMENT CASTING PROCESS FOR HOLLOW COMPONENTS - An investment casting process for a hollow component such as a gas turbine blade utilizing a ceramic core ( | 06-09-2011 |
| 20110132564 | INVESTMENT CASTING UTILIZING FLEXIBLE WAX PATTERN TOOL - An investment casting process wherein the wax pattern tool ( | 06-09-2011 |
| 20110143162 | Process for Manufacturing a Component - A method of manufacturing a component, including providing a three-dimensional computer model of the component to be produced; deconstructing the three-dimensional computer model by defining a plurality of model slices; forming a plurality of metallic foils, where each foil corresponds to a specific model slice; assembling the plurality of formed foils in a tool to form a three-dimensional component stack; and bonding the three-dimensional component stack to form the component. Characteristics of the foils may differ in various portions of the stack, such as being a different material, having a different thickness, or having a different grain orientation. The control of dimensional tolerances of internal structures, such as cooling passages, in three dimensions is devolved into two separate steps of 1) selecting a thickness of each slice/foil, and 2) controlling in two dimensions a material removal process applied to the respective foil. | 06-16-2011 |
