Abstract: An abrasive coating for a metal airfoil tip in a gas turbine engine may include a plurality of grit particles coated with a braze alloy material and configured for attachment to the airfoil tip. The braze alloy may be a nickel base, cobalt base or iron base braze alloy or mixtures thereof, or a titanium base braze alloy.

Abstract: A method for controlled peening includes forming a surface layer on a workpiece by impacting a surface with a tool wherein the tool is under control to form compressive residual stresses in the surface layer. A system for peening a workpiece includes a tool configured to vibrate and an effector operatively connected to control the tool. The tool includes a peening surface. The tool is configured to cause controlled impact between the peening surface and a surface of a workpiece to form a surface layer of the workpiece with compressive residual stresses. The effector is configured to move the tool in multiple axes.

Abstract: What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine. The system includes an axially rotable member including an abrasive tip having a first tensile strength. The system also includes a stationary structure radially exterior and adjacent to the rotable member and including an abradable material. The abradable material includes a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength and a filler material interspersed with the matrix material.

Abstract: A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

Abstract: A turbine engine system comprising a turbine engine component, such as a fan includes a fan casing and a fan blade rotatable within the fan casing. An abradable seal coupled to the fan casing proximate the fan blade. The abradable seal comprising an abradable composite layer including a MAX phase solid and a polymer based abradable composition.

Abstract: An abradable seal includes a seal element that is formed of a polymer matrix with thermally conductive microspheres dispersed through the polymer matrix. The polymer matrix has a polymer matrix thermal conductivity and the microspheres have a microsphere thermal conductivity that is greater than the polymer matrix thermal conductivity.

Abstract: A blade includes a blade body extending from a blade root to an opposed blade tip surface along a longitudinal axis. The blade body defines a pressure side and a suction side. The blade body includes a cutting edge defined where the tip surface of the blade body meets the pressure side of the blade body. The cutting edge is configured to abrade a seal section of an engine case. A method for manufacturing a blade includes forming an airfoil with a root and an opposed tip surface along a longitudinal axis, wherein the airfoil defines a pressure side and a suction side. The method also includes forming a cutting edge where the tip surface of the airfoil meets the pressure side of the airfoil.

Abstract: A disclosed method utilizes virtual representations of gear profiles produced in view of accuracies and capabilities of specific machine and tool combinations to validate profile finishing parameters. The virtual representations are utilized to identify modifications needed to account for process capability and are implemented into the process to change the nominal profile utilized for producing the finished gear profiles. The resulting nominal gear profile accounts for process variations and thereby provides a more accurate and repeatable gear tooth profile.

Abstract: A system and methods are provided for electrochemical grinding a workpiece. In one embodiment, a method includes controlling potentials to grinding tool and the workpiece, controlling applying electrolyte, and controlling grinding of the workpiece by the grinding tool. The method may also include determining screen replacement when there is sufficient metal plated.

Abstract: A fan blade for a gas turbine engine is described. The fan blade may comprise a body portion formed from a metallic material, and it may include a suction side, a pressure side, a leading edge, a trailing edge, and a tip. A coating may be applied to the tip, and the coating may have a thermal conductivity of no more than about 10 watt per meter kelvin. The coating may be a thermal barrier coating comprising yttria-stabilized zirconia.

Abstract: A ceramic shroud seal has a roughed inner surface for contacting a rotating turbomachine component.

Abstract: A method of forming a curved slot in a turbine disk includes the steps of forming a pre-slot in the turbine disk and finishing the pre-slot to form a slot that receives a portion of a turbine blade. The turbine disk including a first face, an opposing second face, and an outer perimeter surface extending between the first face and the opposing second face. The pre-slot includes a first curved wall and a second curved wall that each extend between the first face and the opposing second face. An intersection between the outer perimeter surface and each of the first curved wall and the second curved wall is defined by a curved line.

Abstract: A method for cutting a blade root retention slot in a turbine engine disk element includes forming a precursor slot in the element. The precursor slot has first and second sidewalls and a base. A rotating bit is passed through the precursor slot to machine the base. The bit rotates about an axis off-normal to a direction of passing. A cutting performance of the rotating bit is modeled reflecting a chip trapping intensity parameter and a heat intensity parameter. At least one parameter of the bit and its passing is selected so as to avoid tool loading where removed chips/swarf stick onto the bit.

Abstract: A method of forming a curved slot in a turbine disk includes the steps of forming a pre-slot in the turbine disk and finishing the pre-slot to form a slot that receives a portion of a turbine blade. The turbine disk including a first face, an opposing second face, and an outer perimeter surface extending between the first face and the opposing second face. The pre-slot includes a first curved wall and a second curved wall that each extend between the first face and the opposing second face. An intersection between the outer perimeter surface and each of the first curved wall and the second curved wall is defined by a curved line.

Abstract: A tool is disclosed that has an elongated tool body defining a longitudinal axis and includes a ball-end section having a positive taper angle relative to the longitudinal axis of the tool body, and a relief section that extends rearwardly from the ball-end section and has a negative taper angle relative to the positive taper angle of the ball-end section.

Abstract: A method for forming a component having an abrasive portion includes forming the component and selectively forming a coating on the component using electric spark deposition to form the abrasive portion. A method for coating a blade tip with an abrasive material includes forming a blade having a tip and depositing a coating on the blade tip using electric spark deposition. A method includes providing a casing having an inner diameter surface, locating an abradable coating on a portion of the inner diameter surface, providing a blade configured to rotate within the casing and having a blade tip where the blade tip and the inner diameter surface of the casing form a seal, and depositing an abrasive coating on the blade tip using electric spark deposition so that the abrasive coating and abradable coating interact during rotation of the blade within the casing.

Abstract: A method, an apparatus and a computer for data operation are provided. The method includes: determining, when writing data to a sector of a storage device, whether the sector belongs to an old block for a restore point of the storage device. If so, the method further includes: allocating a new block and writing the data into the new block; creating a table including an address of the old block, an address of the new block and a first identifier, wherein the first identifier has first identification elements corresponding to the sector in the old block and in the new block, respectively, and wherein each of the first identification elements has a first state indicating to read data from the old block during data restoration in the sector and a second state indicating to read data from the new block during data restoration in the sector; and pointing the address of the old block in an address index table for the restore point to the created table.

Abstract: An airfoil for a gas turbine engine is disclosed. The airfoil may include a first side, and a second side opposite the first side. The first side and the second side may extend axially from a leading edge to a trailing edge and radially from a base to a tip. The tip may include an oblique surface between the first side and the second side.

Abstract: A turbine engine system comprising a turbine engine component, such as a fan includes a fan casing and a fan blade rotatable within the fan casing. An abradable seal coupled to the fan casing proximate the fan blade. The abradable seal comprising an abradable composite layer including a MAX phase solid and a polymer based abradable composition.

Abstract: An abradable seal includes a seal element that is formed of a polymer matrix with thermally conductive microspheres dispersed through the polymer matrix. The polymer matrix has a polymer matrix thermal conductivity and the microspheres have a microsphere thermal conductivity that is greater than the polymer matrix thermal conductivity.