Abstract: A gas turbine blade may have a bond coat applied to its surface. A porous substrate may be applied to the bond layer and one or more protective layers may be applied to the bond layer such that the fiber mesh is embedded between the bond layer and the protective layer to prevent creep.

Abstract: A turbine blade assembly is disclosed. In one embodiment, the turbine blade assembly may generally include a turbine blade having a root portion and an airfoil. The airfoil may extend radially from the root portion to an airfoil tip. Additionally, the turbine blade assembly may include a composite rod extending within the turbine blade. The composite rod may include a first end coupled to the airfoil at the airfoil tip and a second end coupled to the root portion. Moreover, the coefficient of thermal expansion of the composite rod may be designed to be less than or equal to the coefficient of thermal expansion of the airfoil.

Abstract: In one aspect, a method for de-noising vibratory data of a test component is disclosed. The method may generally include obtaining data related to a plurality of modeled mode shapes of a finite element model of a test component, obtaining data related to a plurality of experimental mode shapes of the test component from a plurality of non-contact vibration measurement devices and de-noising with a computing device the plurality of experimental mode shapes using the plurality of modeled mode shapes to create a plurality of de-noised mode shapes for the test component.

Abstract: An adaptor assembly for coupling a blade root of a turbine blade to a root slot of a rotor disk is described. The adaptor assembly includes a turbine blade having a blade root and an adaptor body having an adaptor root. The adaptor body defines a slot having an open end configured to receive the blade root of the turbine blade such that the adaptor root of the adaptor body and the blade root of the turbine blade are adjacent to one another when the blade root of the turbine blade is positioned within the slot. Both the adaptor root of the adaptor body and the blade root of the turbine blade are configured to be received within the root slot of the rotor disk.

Abstract: An adaptor assembly for coupling a blade root of a turbine blade to a root slot of a rotor disk is disclosed. The adaptor assembly may generally include an adaptor body having a root configured to be received within the root slot. The adaptor body may also define a slot having an open end configured to receive the blade root. The adaptor body may further define a channel. The adaptor assembly may also include a plate having an outwardly extending foot. The foot may be configured to be received within the channel. Additionally, the plate may be configured to cover at least a portion of the open end of the slot when the foot is received within the channel.

Abstract: A turbine blade assembly is disclosed. In one embodiment, the turbine blade assembly may generally include a turbine blade having a root portion and an airfoil. The airfoil may extend radially from the root portion to an airfoil tip. Additionally, the turbine blade assembly may include a composite rod extending within the turbine blade. The composite rod may include a first end coupled to the airfoil at the airfoil tip and a second end coupled to the root portion. Moreover, the coefficient of thermal expansion of the composite rod may be designed to be less than or equal to the coefficient of thermal expansion of the airfoil.

Abstract: A system for reinforcing a substrate includes a rotary device, a first guide connected to the rotary device, and a form positioned against the first guide. A reinforcement is supplied to wind around the form and against the first guide. A method for reinforcing a substrate includes connecting a first guide to a rotary device and positioning a form on a first side of the first guide. The method further includes winding a reinforcement around the form and against the first side of the first guide.

Abstract: A system includes a rotary machine including, a stator, a rotor configured to rotate relative to the stator, a plurality of axial grooves disposed along a circumference of the stator or the rotor, a plurality of blade segments disposed along the circumference, wherein each blade segment of the plurality of blade segments comprises a blade coupled to a mounting base supported in a respective axial groove of the plurality of axial grooves, and the plurality of blades has a non-uniform blade spacing about the circumference.

Abstract: A system includes a rotary machine with a fluid flow path extending along an axis of the rotary machine, a plurality of airfoils disposed about the axis, and a plurality of spacers disposed about the axis. Each spacer of the plurality of spacers is disposed circumferentially between adjacent airfoils of the plurality of airfoils to define a circumferential spacing of the airfoils about the axis.

Abstract: A system, including a rotary machine including: a stator, a rotor configured to rotate relative to the stator, wherein the rotor comprises a plurality of blades having a non-uniform spacing about a circumference of the rotor.

Abstract: Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component.

Abstract: An article, such as a bucket, a blade, a nozzle, a vane, a strut, a fuel nozzle, a combustion casing, and a transition piece, the article having a damping coating comprising approximately 8 wt % to approximately 15 wt % Y2O3 and approximately 19 wt % to approximately 28 wt % Ta2O5 with the balanced weight of ZrO2 is presented.

Abstract: A method of forming an electrical component is provided. The method comprises preparing a subassembly by electrically connecting an integrated circuit to a flexible circuit; and attaching the subassembly to a multilayer ceramic capacitor having a mounting surface with a curvature deviation exceeding 0.008 inches per inch.

Abstract: A method of forming an electrical component is provided. The method comprises preparing a subassembly by electrically connecting an integrated circuit to a flexible circuit; and attaching the subassembly to a multilayer ceramic capacitor having a mounting surface with a curvature deviation exceeding 0.008 inches per inch.

Abstract: A blade for rotating equipment. The blade includes a root and an airfoil with a leading edge attached to the root. The blade may include a laser shot peened root patch extending along the leading edge and the root.

Abstract: A turbomachine component includes a main body having a surface, and a damping structure mounted to the surface of the main body. The damping structure is formed from a material having a temperature dependent damping characteristic.

Abstract: A method of forming an electrical component is provided. The method comprises preparing a subassembly by electrically connecting an integrated circuit to a flexible circuit; and attaching the subassembly to a multilayer ceramic capacitor having a mounting surface with a curvature deviation exceeding 0.008 inches per inch.

Abstract: Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component.

Abstract: An antenna assembly includes a plurality of antennas for use in wireless communication. A ganging member is provided for ganging the plurality of antennas in a substantially fixed relationship.

Abstract: A method and system for mapping a number of characters in a string, wherein the string comprises a combination of characters representing indexed expressions and a combination of characters representing non-indexed expressions. One embodiment produces a weight array that can be utilized to compare a first and second string having indexed and non-indexed expressions. In one embodiment, a method generates a set of special weights for characters that represent indexed and non-indexed expressions. The method then associates a weight value of an indexed expression with the specific group of characters representing a specific non-indexed expression, and generates a weight array by retrieving a plurality of special weights associated with the specific group of characters representing the specific non-indexed expression and the associated weight value of the indexed expression.