A pressure tool for rotor blade repair including a mobile support system including a support surface, a first bladder support assembly including a first inflatable bladder fixedly mounted to the support surface, a second bladder support assembly including a second inflatable bladder pivotally mounted relative to the support surface, and an activation mechanism operatively coupled to the second bladder support assembly. The activation mechanism is operable to selectively shift the second bladder support assembly relative to the first bladder support assembly. A fluid delivery system is operable to direct a fluid into each of the first inflatable bladder and the second inflatable bladder.

An apparatus and a process for converting a twin spool aero gas turbine engine to an industrial gas turbine engine, where the fan of the aero engine is removed and replaced with an electric generator, a power turbine is added that drives a low pressure compressor that is removed from the aero engine, variable guide vanes are positioned between the high pressure turbine and the power turbine, and a low pressure compressed air line is connected between the outlet of the low pressure compressor and an inlet to the high pressure compressor, where a hot gas flow produced in the combustor first flows through the high pressure turbine, then through the low pressure turbine, and then through the power turbine.

A casing component is configured to form part of a flow path in a turbine. The casing component includes a base made of nodular cast iron, and a repaired region in the base. The repaired region includes a butter layer applied on the base and a fill layer applied on the butter layer.

A method of repairing a component using an additive manufacturing process is presented. The method includes submerging the component into a powder bed so that a portion of the component to be repaired is level with a surface of the powder bed and a protruding portion of the component protrudes above the surface of the powder bed, positioning a split wiper that includes a first wiper segment and a second wiper segment in the powder bed at the surface, advancing a quantity of powder by translating the first wiper segment and the second wiper segment across the surface of the powder bed, and directing a laser beam across the surface to fuse powder particles of the powder bed to the underlying substrate forming a layer of the component. Each of the first wiper segment and the second wiper segment follow a different contour of the protruding portion at the surface.

A mobile machine tool for segmentally machining, in situ, a component, in particular a component of a turbine, which is rotatable about an axis of rotation. The machine tool has a main body, a support element which is held on the main body so as to be movable about a C-axis along a circular-arc-shaped guide path, and a tool module which is held on the support element and is designed to receive a tool. The tool module is located on the support element so as to be linearly movable. A method segmentally machines, in-situ, a component which is mounted in a stationary body so as to be rotatable about an axis of rotation.

A method of reworking an aerospace component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity. The cavity is then at least partially filled with a multiple of layers of discrete laser powder deposition spots of a filler alloy. A cast component for a gas turbine engine includes a cast component non-fusion weldable base alloy with a cavity filled with a multiple of layers of laser powder deposition spots of a filler alloy. The filler alloy may be different than the non-fusion weldable base alloy. A layer of non-fusion weldable base alloy is at least partially within the cavity and over the filler alloy.

The invention relates to a method for repairing a damaged blade tip of a turbine blade which is armor-plated and provided with a blade coating, of a thermal gas turbine. The method according to the invention comprises the steps of removing a blade tip armor plating of the turbine blade at least in the region of the damaged blade tip and producing a repair surface (12), removing only a part of the blade coating of the turbine blade in the region of the repair surface while preserving a part of the blade coating separated from the repair surface (14), restoring the blade tip reinforcement (20), and restoring the blade coating in the region of the repaired blade tip (22). The invention furthermore relates to a device for carrying out such a method.

Turbomachine ring as well as a turbomachine comprising such a ring and a method for repairing such a ring, the turbomachine ring comprising an essentially cylindrical support, including a frontal surface wherein a notch is formed, one or more sectors forming an annulus configured to embody a segment of air stream, each sector comprising a hook portion protruding in the direction of the support and engaging in the notch of the support, and an anti-wear device having a U shaped portion, provided in the notch of the support and pressed at least against the radially external surface of the notch, and a tab portion, continuously extending the U shaped portion, pressed and fastened against the frontal surface of the support.

A gas turbine engine includes a fan that has fan blades wherein the fan delivers airflow to a bypass duct. A gearbox is defined along an engine axis. A low spool is arranged aft of the gearbox and coupled to drive the gearbox. A front center body assembly is defined around the engine axis. A flexible support supports the gearbox relative to the front center body assembly. A bearing package is mounted to the front center body assembly and the low spool. A front wall is mounted to the front center body assembly. The front wall is removable from the front center body assembly to access at least one of the gearbox or the bearing package. The low spool includes a low pressure compressor hub that provides a spline for engaging the bearing package.

This blade repair method has: a first welding step in which overlay welding in which a first welding material is used is performed to form a notched part and a bury a first region positioned on a blade-body side with a first welding material; and a second welding step in which, after the first welding step, overlay welding in which a second welding material is used is performed to form a notched part and bury a second region positioned on a front-surface side of a platform with the second welding material. The high-temperature strength of the second welding material is higher than the high-temperature strength of the first welding material, the weldability of the first welding material is higher than the weldability of the second welding material, and the second region is located in a range from 1.0 mm to 3.0 mm (inclusive) from the front surface of the platform toward the blade body.