Abstract: A device (30) for optimizing the cooling in a gas turbine of the type comprising at least one compressor, equipped with a combustion chamber (10) and an outer casing (16) and inner casing (32), at least one turbine wheel (14), equipped with a series of blades 12), and at least one high-pressure rotor (38), equipped with one or more supporting bearings (34), the compressor being capable of generating cooling air sent to the turbine wheel (14) through a suitable channel (20). On the outer surface of the device (30), there are one or more grooves (26) which allow the passage of additional flow-rates of air from the compressor towards the channel (20), in order to increase the overall cooling air flow towards said turbine wheel (14). The device (30) can be easily installed without the necessity of dismantling the outer casing (16), and is assembled on pre-existing machines in substitution of the vent tube (22) of the seals (36) of the supporting bearings (34).

Abstract: A poppet valve is disclosed that includes a valve body, a poppet guide disposed inside the valve body so as to form a flow passage from an inlet to an outlet of the valve, a poppet shutter disposed inside the poppet guide, and a biasing member to bias the poppet shutter away from the poppet guide toward an inside surface of the flow inlet so as to block the flow passage. The poppet valve further includes at least one discharge hole placing an inner chamber of the poppet guide in flow communication with a region of low static pressure of the flow passage. A method for reducing a closing pressure force acting on a poppet shutter of a poppet valve is also disclosed.

Abstract: Systems and methods for generating transfer functions associated with calculating local stresses on pipe elements by post processing forces and moments of a pipe model representing the piping system. The transfer functions are reusable and allow recalculation with different sets of user data without requiring regeneration of the transfer functions.

Abstract: A method is described for the start-up of a gas turbine comprising the phases of effecting a preliminary purging cycle of the discharge duct (28) of the turbine (20), establishing a predetermined minimum value (FSR1) for the flow of gaseous fuel entering the combustor (14) for a period of time which is adequate for effecting a first attempt at ignition and effecting a first attempt at ignition, effecting an intermediate purging cycle of the discharge duct (28), interrupting the flow of gaseous fuel to the combustor (14), and progressively increasing the value (FSRn) of the flow of gaseous fuel entering the combustor (14), effecting further attempts at ignition until the mixture of air/gaseous fuel has been ignited and the consequent start-up of the turbine (20), or until a predetermined maximum value (FSRmax) of the flow of gaseous fuel has been reached.

Abstract: A torsional mode damping controller system is connected to a converter that drives a drive train including an electrical machine and a non-electrical machine. The controller system includes an input interface configured to receive measured data related to variables of the converter or the drive train and a controller connected to the input interface. The controller is configured to calculate at least one dynamic torque component along a section of a shaft of the drive train based on the measured data from the input interface, generate control data for a rectifier and an inverter of the converter for damping a torsional oscillation in the shaft of the drive train based on the at least one dynamic torque component, and send the control data to the rectifier and to the inverter for modulating an active power exchanged between the converter and the electrical machine.

Abstract: A motor-compressor includes a compressor, an electric motor directly connected to the compressor, magnetic bearings and one gas support located adjacent to a magnetic bearing to seal and support an end of the compressor's rotor. The compressor and the electric motor are integrated in a single unit, being housed in a single box or casing.

Abstract: A torsional mode damping controller system is connected to a converter or placed inside the converter. The converter is driving a drive train including an electrical machine and a non-electrical machine. The controller system includes a first input interface configured to receive a first digital signal from a first phase lock device or a first dynamic observer, a second input interface configured to receive a second digital signal from a second phase lock device or a second dynamic observer, and a controller connected to the first and second input interfaces. The controller is configured to receive the first and second digital signals, compare the first digital signal with the second digital signal, generate control data for a rectifier and/or an inverter of the converter, and send the control data to the rectifier and/or to the inverter.

Abstract: Systems and methods for generating transfer functions associated with calculating local stresses on pipe elements by post processing forces and moments of a pipe model representing the piping system. The transfer functions are reusable and allow recalculation with different sets of user data without requiring regeneration of the transfer functions.

Abstract: Methods and apparatuses for detecting corrosion in one or more blades of a gas turbine system includes a detection head having a shape that conforms to a surface geometry of a filet section of a gas turbine blade, whereby the detection head is operable to move along the axial length of the filet section for detecting corrosion pitting. At least one coil device located within the detection head induces a first magnetic field within an area of the filet in contact with the detection head. A receiver device is adapted to detect a signal corresponding to a second magnetic field received from the area of the filet exposed to the first magnetic field, where the second magnetic field is generated by induced currents in the area by the first magnetic field.

Abstract: A centrifugal impeller for a turbomachine is provided. The centrifugal impeller comprises a plurality of aerodynamic vanes, each of the aerodynamic vanes having internal walls on which is associated a fabric element.

Abstract: Protection device for a stator of a turbine of the type comprising a series of annular sectors constrained to each other by means of connection means, each sector of the series of sectors comprises a first surface, suitable for contacting the stator which has at least one cavity for the cooling of the corresponding sector, and a second surface which faces a rotor of the turbine. In a rest configuration in which the turbine is not operating, the second surface of each sector has an axial section having an eccentricity with respect to the trace of the rotation axis of the turbine, whereas in an operating configuration in which the turbine is operating under regime conditions, the second surface of each sector has an axial section which is centered with the trace of the rotation axis of the turbine.

Abstract: Overhung axial compressor, chemical reactor and method for compressing a fluid. The overhung axial compressor includes a casing configured to be vertically split along a vertical axis for access to an inside of the casing and a removable cartridge. The removable cartridge is configured to fit inside the casing and to be detachably attached to the casing. The removable cartridge includes a shaft disposed along a horizontal axis, the shaft being configured to rotate about the horizontal axis, a bearing system attached to the removable cartridge and configured to rotationally support a first end of the shaft, and plural blades disposed toward a second end of the shaft such that the second end is overhung inside the casing. The compressor also includes a guide vane mechanism configured to connect to the removable cartridge, the guide vane mechanism being configured to adjust a flow of a fluid to the plural blades.

Abstract: Methods and systems providing for characterizing turbine blades, including characterizing the dynamics of one or more turbine blades or stages of a stage in terms of natural frequencies, normalized response intensity, and/or stage modal shape or nodal configuration. Such methods and systems comprise fluid (e.g., oil) excitation of bladed disks and quantitative modeling of the fluid excitation. Additionally or alternatively, such methods and systems may provide for analyzing modal shape or nodal configuration of a bladed disk (e.g., a turbine stage) based on a phase analysis of strain signals acquired from a bladed disk subjected to a fluid excitation, wherein the modal shape or nodal configuration corresponds to modes of blades coupled through a disc or shrouding.

Abstract: A mold for a centrifugal impeller for a turbomachine is provided. The mold comprises at least one annular insert, wherein the annular insert comprises a plurality of aerodynamic vane inserts configured to reproduce an annular assembly of aerodynamic vanes of a finished centrifugal impeller.

Abstract: A torsional-mode damping system includes a torque sensor, a torsional damper connected to the torque sensor, a VFD controller connected to the torsional damper, and a VFD converter connected to the VFD controller, the VFD converter being configured to control an electric power supplied to the electric motor based on VFD signals generated by the VFD controller, the VFD signals being modified by a torque-correcting signal so as to dampen torsional vibrations at a natural frequency of a compression train.

Abstract: System and method for fusing a chaplet to a casting. The method includes placing the chaplet on an upper surface of a mold; distributing a heater around the chaplet such that the heater is not exposed to the casting; placing a core on the chaplet such that the mold and the core define a component of a machine; heating the chaplet with the heater to a predetermined temperature; and pouring the casting in the mold, around the core and the chaplet, when the chaplet is at the predetermined temperature.

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 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: Method and impeller cover for protecting an impeller from damage. The impeller cover includes a removable body having a first face and a second face opposing the first face, the second face being configured to match a front face of the impeller of the compressor, and further having a frontal portion covering an entire frontal portion of the impeller of the compressor, and a fixing mechanism connected to the removable body and being configured to fix the impeller cover to the impeller of the compressor. The impeller cover is disposable.

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).