Abstract: A blade for fluid catalytic cracking (FCC) flue hot gas expander with a layer of hard abrasive material localized on the blade tip that contributes to reducing the accumulation of FCC catalyst residuals in the expander.

Abstract: The steam turbine has a plurality of expansion stages and stator blades upstream at least one of the expansion stages; in order to regulate steam flow inside the steam turbine and maximize turbine efficiency, the angular positions of the stator blades are controlled for example by an external control unit through e.g. a command rod during operation of the steam turbine.

Abstract: A method for manufacturing a stage of a steam turbine comprising the steps of milling a block of material to define a sector having a plurality of blades, each blade having an external surface; machining an opening in the external surface of at least one of the blades; machining a cavity in fluid communication with the opening; the step of machining the cavity being performed by wire electric discharge machining.

Abstract: A turbomachine assembly is shown, including a rotor and a ring of blades mounted on the rotor. Each blade includes an airfoil portion and a root portion inserted in a circumferential blade-retaining groove of the rotor. The blade-retaining groove includes an enlarged groove portion. The blades in the enlarged groove portion are rotatable around a respective, generally radial axis, to take a position of minimum tangential dimension. At least one removable insert is arranged along the enlarged groove portion, between the root portions of the blades located in the enlarged groove portion and a side wall of the blade-retaining groove, to force and lock the blades in a final assembled arrangement.

Abstract: A method for manufacturing a stage of a steam turbine comprising the steps of milling a block of material to define a sector having a plurality of blades, each blade having an external surface; machining an opening in the external surface of at least one of the blades; machining a cavity in fluid communication with the opening; the step of machining the cavity being performed by wire electric discharge machining.

Abstract: A turbomachine assembly is shown, including a rotor and a ring of blades mounted on the rotor. Each blade includes an airfoil portion and a root portion inserted in a circumferential blade-retaining groove of the rotor. The blade-retaining groove includes an enlarged groove portion. The blades in the enlarged groove portion are rotatable around a respective, generally radial axis, to take a position of minimum tangential dimension. At least one removable insert is arranged along the enlarged groove portion, between the root portions of the blades located in the enlarged groove portion and a side wall of the blade-retaining groove, to force and lock the blades in a final assembled arrangement.

Abstract: A high velocity spray method for treating the surface of a component, the method comprises the steps of heating a first portion of an inert gas up to a spray temperature comprised between 550° C. and 800° C.; preparing a powder material having a composition including Co at a mass percentage comprised between 15% and 70%; preparing a mixture between the powder material and a second portion of inert gas; mixing the first portion of inert gas and the mixture of gas and powder in a spray gun in order to create a spray jet; directing said spray jet towards the surface to be treated in order to deposit a coating of the material including Co.

Abstract: A blade of a turbomachine comprises an airfoil portion; the airfoil portion extends longitudinally; the airfoil portion is defined laterally by an external surface; the airfoil portion has a 3D and twisted shape and has an internal cavity; the blade is in a single piece. Furthermore, the blade is designed for a rotor or stator array; the rotor or stator defines a radial direction and an axial direction; the external surface of the airfoil portion has a leading edge and a trailing edge; the leading edge and/or the trailing edge shifts backward or forward in the axial direction moving in the radial direction; the internal cavity extends along substantially the whole longitudinal length of the airfoil portion. Additive manufacturing is particularly effective and advantageous for such blade.

Abstract: A hollow blade for a turbomachine comprises an airfoil portion; the airfoil portion extends longitudinally for a length; the airfoil portion is defined laterally by an external surface; the airfoil portion has at least one internal cavity extending along said length and defined laterally by an internal surface; the airfoil portion has a set of channels extending from the external surface to the internal surface; the openings of said channels on said external surface are aligned along a curved line that reflects an isobar on said external surface.

Abstract: The method is used for manufacturing a turbomachine blade that comprises an airfoil portion and is divided into two parts at an intermediate region of the airfoil portion; each of the two parts of the airfoil portion is obtained by additive manufacturing; the two parts are joined by brazing.

Abstract: A blade is mountable to a disc. The blade comprises a blade platform and a blade root extending from the blade platform. The blade root comprises a first hook and a second hook, a first neck between the first hook and the blade platform, and a second neck between the first hook and the second hook. Each hook comprises a contact surface and a non-contact surface. An angle between each contact surface and each non-contact surface is optimized to reduce local stresses.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: Vapor turbine operating with geothermal vapors containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of rotor blades made of a nickel alloy containing a quantity of nickel ranging from 55% to 59% by weight to avoid the washing of the geothermal vapors, maintaining a high useful life of the series of rotor blades and vapor turbine.

Abstract: A rotating blade for a steam turbine includes a root section and an airfoil section contiguous with the root section. The airfoil section is shaped to optimize aerodynamic performance while providing optimized flow distribution and minimal centrifugal and bending stresses. The blade also includes a tip section continuous with the airfoil section, and a cover formed as part of the tip section. The cover defines a radial seal that serves to minimize tip losses. The rotating blade is capable of running at operating speeds between 5626 and 11250 rotations per minute.

Abstract: A blade is mountable to a disc. The blade comprises a blade platform and a blade root extending from the blade platform. The blade root comprises a first hook and a second hook, a first neck between the first hook and the blade platform, and a second neck between the first hook and the second hook. Each hook comprises a contact surface and a non-contact surface. An angle between each contact surface and each non-contact surface is optimized to reduce local stresses.

Abstract: Vapour turbine operating with geothermal vapours containing corrosive agents such as chlorides and/or sulfides in particular. The turbine comprises a series of rotor blades made of a nickel alloy containing a quantity of nickel ranging from 55% to 59% by weight to avoid the washing of the geothermal vapours, maintaining a high useful life of the series of rotor blades and vapour turbine.