Abstract: A turbomachine includes a compressor having a cartridge that is configured to slide in and out of an external casing. The turbomachine further includes an electrical motor having a motor shaft configured to be connected to the compressor shaft. A conduit is configured to extend through the statoric part of the compressor or the motor, from a first magnetic bearing to the second magnetic bearing. The conduit includes conduit electrical cables provided inside the conduit and extending from a first end of the conduit to a second end of the conduit; and electrical cables connecting one of the first and second magnetic bearings to an external connector via the conduit electrical cables of the conduit.

Abstract: A motor includes a casing having a cavity, a stator configured to be attached to an inside of the cavity, an elastic cone configured to be attached to a first end of the casing, a rigid cone configured to be attached to a second end of the casing that is opposite to the first end, a non-metallic part configured to be attached to the elastic cone and the rigid cone, and a rotor provided inside the cavity and configured to rotate inside the stator. The casing, the elastic cone, the rigid cone, and the non-metallic part form a hermetic enclosure in which the entire stator is enclosed and the hermetic enclosure is configured to hold a cooling fluid that cools the stator and also to prevent the cooling fluid to reach the rotor.

Abstract: A compressor unit for processing a working fluid comprising a compressor inside a housing to compress the working fluid wherein a collection chamber is fluidly coupled with a working fluid inlet of said housing.

Abstract: A turbomachine is provided. The turbomachine comprises a compressor, at least two magnetic bearings provided at opposite ends of a compressor shaft, a motor having a motor shaft, a first electrical cable having a first end, a second end, an internal core section and an outer sheath section with the internal core section and the outer sheath section extending from the first end to the second end, a first connector configured to connect the first end to the first magnetic bearing, wherein the first connector is welded or brazed to the first end to both the internal core section and the outer sheath section, and a second connector configured to connect the second end to the first external connection, wherein the second connector is welded or brazed to the second end to both the internal core section and the outer sheath section.

Abstract: A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the first and second platforms and connected thereto, a portion of an inside surface of the first platform or the second platform being scalloped so as to increase a throat area of the nozzle segment in order to increase the nozzle segment's mass flow rate handling capability.

Abstract: A balancing group (22) is described for the rotor of a fluid rotary machine (10), wherein the rotor is of the type comprising at least one shaft (16) equipped with an internal pass-through hole (20) which develops along the longitudinal axis (A) of the shaft (16). The balancing group (22) includes at least a first inner element (24) and at least a second outer element (26), the first inner element (24) being suitable for being engaged by interference, in the direction of the longitudinal axis (A), inside the second outer element (26). The balancing group (22) thus formed is suitable for being inserted, in the direction of the longitudinal axis (A), inside the pass-through hole (20) of the shaft (16).

Abstract: A turbomachine includes a compressor having a cartridge that is configured to slide in and out of an external casing. The turbomachine further includes an electrical motor having a motor shaft configured to be connected to the compressor shaft. A conduit is configured to extend through the statoric part of the compressor or the motor, from a first magnetic bearing to the second magnetic bearing. The conduit includes conduit electrical cables provided inside the conduit and extending from a first end of the conduit to a second end of the conduit; and electrical cables connecting one of the first and second magnetic bearings to an external connector via the conduit electrical cables of the conduit.

Abstract: A method for assembling turbomachinery having combined particle separation device and flow regulating device is provided. The turbomachinery includes a casing; a compressor attached to an inside of the casing, the compressor having a shaft supported by bearings; and a cooling system mounted inside the casing and configured to cool the bearings of the compressor with a cooling fluid. The cooling system includes a particle separation device configured to separate particles from the cooling fluid, and a flow regulation device that fluidly communicates with the particle separation device without contacting the particle separation device. The flow regulation device is disposed adjacent to the particle separation device within a wall of the casing.

Abstract: A nozzle segment is disclosed that includes a first platform configured to be connected with a casing of a gas turbine engine, a second platform configured to be connected with the casing, the second platform being disposed apart from the first platform in a radial direction of the gas turbine engine, and a plurality of blades disposed between the first and second platforms and connected thereto, a portion of an inside surface of the first platform or the second platform being scalloped so as to increase a throat area of the nozzle segment in order to increase the nozzle segment's mass flow rate handling capability.

Abstract: A balancing group (22) is described for the rotor of a fluid rotary machine (10), wherein the rotor is of the type comprising at least one shaft (16) equipped with an internal pass-through hole (20) which develops along the longitudinal axis (A) of the shaft (16). The balancing group (22) includes at least a first inner element (24) and at least a second outer element (26), the first inner element (24) being suitable for being engaged by interference, in the direction of the longitudinal axis (A), inside the second outer element (26). The balancing group (22) thus formed is suitable for being inserted, in the direction of the longitudinal axis (A), inside the pass-through hole (20) of the shaft (16).

Abstract: A system for connecting a low-pressure jet to a transition duct in a gas turbine, in which the said low-pressure jets are arranged in sectors of two or three stator blades and are filled on to the ring of the jets. The platforms of the jets are provided with a channel inside which the transition duct is positioned by means of an edge. Furthermore, centering between the transition duct and the ring of the jets is achieved directly using centering means at three or more points.

Abstract: A system for connecting a low-pressure jet (12) to a transition duct (149 in a gas turbine, in which the said low-pressure jets (12) are arranged in sectors of two or three stator blades and are filled on to the ring of the jets. The platforms (11) of the jets (12) are provided with a channel (13) inside which the transition duct (14) is positioned by means of an edge (15). Furthermore, centring between the transition duct (14) and the ring of the jets (12) is achieved directly using centring means at three or more points on the rings of the jets (12).

Abstract: A combustion chamber for gas turbines comprises an inner liner (12) and an outer liner (11), wherein the inner liner (12) is substantially concentric relative to the outer liner (11), such as to define an annular inner space (30), and wherein a shield (13) is provided at the output of each of the burners. The specific feature of the invention consists in the fact that each of the shields (13) comprises a single metal plate part, and that the liners (11, 12) have a plurality of holes (20, 21), in sections adjacent to the longitudinal development of the shield (13), such as to define gaps (60, 61) for the circulation of air.

Abstract: A device (31) for connection of a nozzle (23) of a pre-mixing chamber (11) of a gas turbine, to a housing (12) of the pre-mixing chamber (11) comprises a flange (33) which clasps and retains the nozzle (23). The flange (33) is connected in a detachable manner to the housing (12) of the pre-mixing chamber (11), so as to render the nozzle (23) integral with the housing (12) of the pre-mixing chamber (11).

Abstract: A device for securing blades of the first stage of a gas turbine wherein the blades having cooling passages for flowing cooling air from the blade roots towards the blade airfoils. A plurality of plates, each of which has at least one U-shaped projection, engages a corresponding U-shaped groove in the surface of a rotor disc of the first stage. Each plate is interposed between two adjacent first stage blades to secure the blades axially. Second stage turbine blades are secured against axial movement by a plurality of plates, each of which is interposed between the end portion of the foot of a corresponding blade and the turbine disc. Each of the latter plates is provided with ends to secure the blade axially.

Abstract: A pre-mixing chamber (10) for gas turbines, wherein the gas turbine is of the type which comprises at least one compressor connected to the turbine, and a combustion chamber, wherein the combustion chamber has a converging portion (12), positioned such as to give rise to combustion inside the combustion chamber, and wherein the pre-mixing chamber (10) has a plurality of pipes (19) provided with holes (20), which open into the combustion chamber on a front portion of the body of the pre-mixing chamber (10), in order to generate a series of pilot flames, which are appropriately regulated, in order to stabilise a main flame, which is primed inside the combustion chamber, in which a front area of the converging portion (12) of the pre-mixing chamber (10) has at least one circular groove (28) provided at the holes (20) which belong to the pies (19).

Abstract: A support and locking device for nozzles of a high-pressure stage in gas turbines comprises a plurality of groups of stator vanes, which are associated with a plurality of outer sealing plates, for connection of the groups to the outer liner of the combustion chamber, and are associated with a plurality of inner sealing plates, for connection of the groups to the inner liner of the combustion chamber. Each of the groups of stator vanes is locked by an inner ring, and the ring has a first series of outer holes to reinforce this locking, and a second series, of inner, through holes, which are provided in an inner extension of the ring and are used to secure the ring itself to the structure of the gas turbine.

Abstract: The present invention relates to a liquid fuel injector (10) for burners in gas turbines, of the type used inside burners which are provided with a pre-mixing chamber (62) and an element (13) to create turbulence in the flow of compressed air obtained from the compressor of the gas turbine. The injector (10) comprises a body (11) which ends in a tip (12) and is provided with at least one duct (25) for passage of the fuel, and ducts (48, 58) for the inflow of compressed air from the compressor of the turbine, wherein the duct (25) for the fuel and the ducts (48, 58) for the compressed air end in respective outlet holes. The tip (12) of the injector (10) ends at the median part of the converging portion (61) of the pre-mixing chamber (62).