Abstract: A ceramic matrix composite (“CMC”) component, such as a turbine blade for a combustion turbine engine that has a fiber-reinforced, solidified ceramic substrate. The substrate has an inner layer of fibers, for enhancing structural strength of the component. An outer layer of fibers defines voids therein. A thermal barrier coat (“TBC”) is applied over and coupled to the outer layer fibers, filling the voids. The voids provide increased surface area and mechanically interlock the TBC, improving adhesion between the fiber-reinforced ceramic substrate and the TBC.

Abstract: Engineered groove features (EGFs) are formed within thermal barrier coatings (TBCs) of turbine engine components. The EGFs are advantageously aligned with likely stress zones within the TBC or randomly aligned in a convenient two-dimensional or polygonal planform pattern on the TBC surface and into the TBC layer. The EGFs localize thermal stress- or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. Propagation of a crack is arrested when it reaches an EGF, so that it does not cross over the groove to otherwise undamaged zones of the TBC layer. In some embodiments, the EGFs are combined with engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC.

Abstract: Turbine and compressor casing abradable component embodiments for turbine engines vary localized porosity or abradability through use of holes or dimple depressions of desired polygonal profiles that are formed into the surface of otherwise monolithic abradable surfaces or rib structures. Abradable porosity within a rib is varied locally by changing any one or more of hole/depression depth, diameter, array pitch density, and/or volume. In various embodiments, localized porosity increases and corresponding abradability increases axially from the upstream or forward axial end of the abradable surface to the downstream or aft end of the surface. In this way, the forward axial end of the abradable surface has less porosity to counter hot working gas erosion of the surface, while the more aft portions of the abradable surface accommodate blade cutting and incursion with lower likelihood of blade tip wear.

Abstract: A hybrid component (45) is provided including a plurality of laminates (10) stacked on one another to define a stacked laminate structure (58). The laminates (10) include a ceramic matrix composite material (22) and at least one opening (24) defined therein. A metal support structure (56) may be additively manufactured through each opening (24) so as to extend through the stacked laminate structure (58).

Abstract: The invention relates to a method for dual curing a RMA crosslinkable resin coating, to RMA crosslinkable compositions and to resins for use in the method.

Abstract: The invention relates to RMA crosslinkable coating composition, a method for the preparation thereof and a resulting coating having easy to clean properties useful in applications like graffiti resistant, sanitisable coatings and in flooring, said composition comprising RMA crosslinkable component with at least 2 RMA donor groups and at least 2 RMA acceptor groups characterized by having fatty components selected from the group of fatty acids, fatty alcohols, fatty amines, fatty thiols and dimeric fatty acid in an amount represented by an Oil Content OC between 0, preferably 4 and 40 wt %, and crosslinking density XLD of at least 1.4 a glass transition Tg of at least 290 in combination providing a easy to clean value ?E less than 20. The invention also relates to RMA crosslinkable fatty resins for use in RMA crosslinkable top coatings.

Abstract: The invention relates to the use of Real Michael Addition (RMA) crosslinkable composition for the preparation of a floor coating, to special RMA crosslinkable compositions with long working time and very short service time and low VOC and to specific floor compositions, in particular for use in high build floor coating applications.

Abstract: A process of directly coating a metal substrate and curing the coating using radiation sources such as UV radiation having a wavelength of 200 nm and above. Furthermore, compositions of the invention can be used as a tie-coat for coatings that do not bond well directly to various metal substrates.

Abstract: An oxide and non-oxide based ceramic matrix composite (“CMC”) component for a combustion turbine engine has a solidified ceramic core with a three-dimensional preform of ceramic fibers, embedded therein. Engineered surface features (“ESFs”) are cut into an outer surface of the core and fibers of the preform. A thermal barrier coat (“TBC”) is applied over and coupled to the core outer surface and the ESFs. The ESFs provide increased surface area and mechanically interlock the TBC, improving adhesion between the ceramic core and the TBC.

Abstract: Turbine and compressor casing abradable component embodiments for turbine engines vary localized porosity or abradability through use of holes or dimple depressions of desired polygonal profiles that are formed into the surface of otherwise monolithic abradable surfaces or rib structures. Abradable porosity within a rib is varied locally by changing any one or more of hole/depression depth, diameter, array pitch density, and/or volume. In various embodiments, localized porosity increases and corresponding abradability increases axially from the upstream or forward axial end of the abradable surface to the downstream or aft end of the surface. In this way, the forward axial end of the abradable surface has less porosity to counter hot working gas erosion of the surface, while the more aft portions of the abradable surface accommodate blade cutting and incursion with lower likelihood of blade tip wear.

Abstract: A hybrid component is provided including a plurality of laminates stacked on one another to define a stacked laminate structure. The laminates include a ceramic matrix composite material having certain features, such as a matrix porosity characteristic and a hierarchical fiber architecture, and at least one opening defined therein. A metal support structure may be arranged through each opening so as to extend through the stacked laminate structure.

Abstract: Methods for laser additive manufacture are disclosed in which a plurality of powder layers (48, 50 and 52) are delivered onto a working surface (54A) to form a multi-powder deposit containing at least two adjacent powders layers in contact, and then applying a first laser energy (74) to a first powder layer (48) and a second laser energy (76) to a second powder layer (52) to form a section plane of a multi-material component. The multi-powder deposit may include a flux composition that provides at least one protective feature. The shapes, intensities and trajectories of the first and second laser energies may be independently controlled such that their widths are less than or equal to widths of the first and second powder layers, their intensities are tailored to the compositions of the powder layers, and their scan paths define the final shape of the multi-material component.

Abstract: Heat insulating layered systems should have a long service life in addition to excellent heat-insulating properties. Disclosed in an inventive layered system consisting of an external ceramic layer that has a mixed crystal consisting of gadolinium zirconate and gadolinium hafnate.

Abstract: A thermal barrier coating including a two layered ceramic barrier coating, an inner ceramic layer and an outer ceramic layer, is provided. The thermal barrier coating has different thicknesses on different places of the component. In addition, the thickness of the inner ceramic layer and the thickness of the outer ceramic layer vary in relation to one another.

Abstract: A thermal barrier coating (TBC) with depth-varying material properties is formed on a turbine component. Exemplary depth-varying material properties include physical ductility, strength and thermal resistivity that vary from the TBC layer inner to outer surface. Exemplary ways to modify physical properties include application of plural separate overlying layers of different material composition or by varying the applied material composition during the application of the TBC layer. Various embodiment described herein also apply a calcium-magnesium-aluminum-silicon (CMAS)-retardant material over the TBC layer to retard reaction with or adhesion of CMAS containing combustion particulates to the TBC layer. In other embodiments the CMAS retardant material is also applied within engineered groove features (EGFs) that are formed in the TBC surface.

Abstract: Thermal barrier coatings (TBCs) for turbine engine components are applied over engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC. The ESFs help anchor the TBC layer and/or localize cracks that are bounded by one or more of the ESFs. During engine operation the ESFs arrest thermal stress-or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. In some embodiments, the ESFs are combined with engineered groove features that are formed in the TBC.

Abstract: Engineered groove features (EGFs) are formed within thermal barrier coatings (TBCs) of turbine engine components. The EGFs are advantageously aligned with likely stress zones within the TBC or randomly aligned in a convenient two-dimensional or polygonal planform pattern on the TBC surface and into the TBC layer. The EGFs localize thermal stress- or foreign object damage (FOD)-induced crack propagation within the TBC that might otherwise allow excessive TBC spallation and subsequent thermal exposure damage to the turbine component underlying substrate. Propagation of a crack is arrested when it reaches an EGF, so that it does not cross over the groove to otherwise undamaged zones of the TBC layer. In some embodiments, the EGFs are combined with engineered surface features (ESFs) that are formed in the component substrate or within intermediate layers applied between the substrate and the TBC.

Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section ridges that reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments at least one angularly oriented first groove formed in the ridge plateau is adapted for angular orientation upstream a turbine blade rotation direction to resist blade tip airflow leakage and the ridges are separated by second grooves that are skewed relative to the respective ridge plateaus and the substrate that are also adapted for orientation upstream the turbine blade rotation direction to resist blade tip airflow leakage.

Abstract: Provided are ultraviolet (UV)-curable polyols and polyurethane compositions made by reacting the inventive polyol with an isocyanate. The inventive ultraviolet (UV)-curable polyol is made by co-polymerizing an alkylene oxide, an unsaturated carboxylic acid or anhydride and a hydroxy functional compound in the presence of a double metal cyanide (DMC) complex catalyst such that the polyol has an ultra-low level of unsaturation. The inventive polyols may be used to produce prepolymers, which in turn may be useful in making thin films which in turn may provide such items as medical examination gloves and scientific gloves. The inventive ultraviolet (UV)-curable polyurethane compositions may also find use in or as coatings, adhesives, sealants, elastomers and the like.

Abstract: Turbine and compressor casing abradable component embodiments for turbine engines, with composite grooves and vertically projecting asymmetric non-parallel walls or trapezoidal cross section ridges that reduce, redirect and/or block blade tip airflow leakage downstream into the grooves rather than from turbine blade airfoil high to low pressure sides. In some embodiments at least one angularly oriented first groove formed in the ridge plateau is adapted for angular orientation upstream a turbine blade rotation direction to resist blade tip airflow leakage and the ridges are separated by second grooves that are skewed relative to the respective ridge plateaus and the substrate that are also adapted for orientation upstream the turbine blade rotation direction to resist blade tip airflow leakage.