Abstract: An engine control system includes a first user control lever configured for rotational movement between a first control position and a second control position and a second user control lever configured for rotational movement between a third control position and a fourth control position. The first user control lever is configured for operational control of an engine in a first control mode and the second user control lever is configured for operational control of the engine in a second control mode, such as a backup mode. A mechanical link couples the first user control lever to the second user control lever with at least one angular offset. As a result of the angular offset, the second user control lever can be maintained in a safe operating position relative to the first user control lever position.

Abstract: A gas turbine fuel nozzle for a combustor of a gas turbine engine comprises a sleeve with an internal duct for premixed fuel gas flow; it further comprises a flame ionization sensor located on the sleeve externally to the duct; typically, the combustor has a single annular-shaped chamber.

Abstract: An electric motor assembly to supply torque is disclosed where the assembly includes a stator modules having a plurality of stator windings, each stator winding configured to receive high-voltage, alternating current; a rotor assembly, each rotor assembly having a hub and plurality of magnets arranged on the hub, the plurality of magnets each having magnetic north and south poles where the plurality of magnets are arranged along an outer periphery of the hub to alternate the magnetic north and south poles; and a main shaft to supply the torque, wherein at least one of the one or more rotor assemblies is configured to rotate the main shaft, and the at least one of the one or more rotor assemblies is associated with and concentrically contained within the one or more stator modules, the at least one of the one or more rotor assemblies being rotatable relative to the one or more stator modules

Abstract: A compressed-air energy-storage system, comprising: a variable-nozzle expander configured to receive an airflow at a first pressure and partially expand said airflow at a second pressure, said second pressure being lower than said first pressure, expansion of said airflow in said variable-nozzle expander producing useful mechanical power; a heat generator component configured to receive a fuel and a partially expanded airflow from the variable-nozzle expander; and a turbine configured to receive combustion gas from the heat generator component and expand the combustion gas producing useful mechanical power.

Abstract: An engine control system includes a first user control lever configured for rotational movement between a first control position and a second control position and a second user control lever configured for rotational movement between a third control position and a fourth control position. The first user control lever is configured for operational control of an engine in a first control mode and the second user control lever is configured for operational control of the engine in a second control mode, such as a backup mode. A mechanical link couples the first user control lever to the second user control lever with at least one angular offset. As a result of the angular offset, the second user control lever can be maintained in a safe operating position relative to the first user control lever position.

Abstract: Method, system and axial multistage expander including a casing and a plurality of stages. A stage includes a stator part connected to the casing and having plural statoric airfoils, and a rotor part configured to rotate relative to the stator part and having plural rotoric airfoils. The axial multistage expander also includes a support mechanism connected to the casing and configured to rotatably support the rotor part. Rotoric airfoils of at least one stage of the plurality of stages are configured to rotate with a speed different from rotoric airfoils of the other stages. The stator part, the rotor part and the support mechanism of the plurality of stages are provided inside the casing.

Abstract: A gas turbine fuel nozzle for a combustor of a gas turbine engine comprises a sleeve with an internal duct for premixed fuel gas flow; it further comprises a flame ionization sensor located on the sleeve externally to the duct; typically, the combustor has a single annular-shaped chamber.

Abstract: A turbine comprising a rotatable rotor and a pressure chamber; a wall of the pressure chamber is arranged to act on the rotor so that to balance thrust exerted by the rotor when it rotates; a conduit connects the pressure chamber and arranged to a pressure source; a valve associated to the conduit may open and close the conduit; the valve is arranged to open automatically when the pressure upstream of the valve exceeds a first predetermined threshold value; in this way, when the load of the turbine is high excessive thrust is balanced because of the higher pressure in the pressure chamber.

Abstract: A vessel of a heat storage and release apparatus, the vessel comprises a shell comprising a metallic material, the shell having an elongated shape with a first end region and a second end region remote from the first end region, and an internal surface defining a cavity configured to contain a heat storage and release device and to guide gas-flow; a first opening through the shell for a flow of gas at high temperature and high pressure, the first opening being located in the first end region; a second opening through the shell for a flow of gas at low temperature and high pressure, the second opening being located in the second end region; and a lining of thermally insulating material adjacent to the internal surface and only partially covering the internal surface, the lining being located at least in the first end region.

Abstract: Method, system and axial multistage expander including a casing and a plurality of stages. A stage includes a stator part connected to the casing and having plural statoric airfoils, and a rotor part configured to rotate relative to the stator part and having plural rotoric airfoils. The axial multistage expander also includes a support mechanism connected to the casing and configured to rotatably support the rotor part. Rotoric airfoils of at least one stage of the plurality of stages are configured to rotate with a speed different from rotoric airfoils of the other stages. The stator part, the rotor part and the support mechanism of the plurality of stages are provided inside the casing.

Abstract: A compressed-air energy-storage system, comprising: a variable-nozzle expander configured to receive an airflow at a first pressure and partially expand said airflow at a second pressure, said second pressure being lower than said first pressure, expansion of said airflow in said variable-nozzle expander producing useful mechanical power; a heat generator component configured to receive a fuel and a partially expanded airflow from the variable-nozzle expander; and a turbine configured to receive combustion gas from the heat generator component and expand the combustion gas producing useful mechanical power.

Abstract: A method is described for controlling load variations in a gas turbine. The method comprises reducing the flow of gaseous fuel entering the combustor to a predefined minimum value, if an increase is observed in the rotation regime of said turbine above a predefined maximum value and a total reduction in the load, activating a selective feeding sequence of the burners if the turbine is operating in normal functioning or premixed flame mode, modifying the angulation of the adjustable stator vanes, in order to reduce the speed rate of the compressor, and opening one or more anti-surge valves and one or more overboard bleeds, in order to reduce the air flow at the inlet of the combustor.

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 vessel of a heat storage and release apparatus, the vessel comprises a shell comprising a metallic material, the shell having an elongated shape with a first end region and a second end region remote from the first end region, and an internal surface defining a cavity configured to contain a heat storage and release device and to guide gas-flow; a first opening through the shell for a flow of gas at high temperature and high pressure, the first opening being located in the first end region; a second opening through the shell for a flow of gas at low temperature and high pressure, the second opening being located in the second end region; and a lining of thermally insulating material adjacent to the internal surface and only partially covering the internal surface, the lining being located at least in the first end region.

Abstract: Method, system and axial multistage expander including a casing and a plurality of stages. A stage includes a stator part connected to the casing and having plural statoric airfoils, and a rotor part configured to rotate relative to the stator part and having plural rotoric airfoils. The axial multistage expander also includes a support mechanism connected to the casing and configured to rotatably support the rotor part. Rotoric airfoils of at least one stage of the plurality of stages are configured to rotate with a speed different from rotoric airfoils of the other stages. The stator part, the rotor part and the support mechanism of the plurality of stages are provided inside the casing.

Abstract: A method and apparatus are described for controlling the combustion in a gas turbine. The method includes measuring, with one or two calorimeters, the temperature, calorific value and relative density of a gaseous fuel in order to determine the Wobbe index, comparing the Wobbe index value measured with a predefined Wobbe index value for the gaseous fuel and regulating the temperature of the gaseous fuel with at least one heat exchanger in order to reach the predefined Wobbe index value. The method may also include using a second gaseous fuel, having a different Wobbe index from the gaseous fuel, or a fuel obtained by mixing the gaseous fuel and the second gaseous fuel, according to arbitrary proportions and variable with time.

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 method is described for controlling load variations in a gas turbine. The method comprises reducing the flow of gaseous fuel entering the combustor to a predefined minimum value, if an increase is observed in the rotation regime of said turbine above a predefined maximum value and a total reduction in the load, activating a selective feeding sequence of the burners if the turbine is operating in normal functioning or premixed flame mode, modifying the angulation of the adjustable stator vanes, in order to reduce the speed rate of the compressor, and opening one or more anti-surge valves and one or more overboard bleeds, in order to reduce the air flow at the inlet of the combustor.

Abstract: A method is described for the controlled purging of the fuel feeding system in the combustor of a gas turbine comprising at least one compressor, capable of compressing the air introduced into it through an inlet duct, at least one combustor, in which said compressed air is mixed and combusted with a gaseous fuel coming from a feeding duct, and at least one turbine, capable of transforming the energy of the combusted gas coming from said combustion chamber into work energy which can be exploited for activating one or more operating machines. The combustor is equipped with one or more burners, each equipped with at least one pilot injector and one or more main injectors for the adduction of the gaseous fuel inside the burner. The method comprises purging at least part of the main injectors and relative manifolds with a stream of gaseous fuel when the turbine is in diffusive flame functioning mode.

Abstract: A method and apparatus are described for controlling the combustion in a gas turbine. The method includes measuring, by means of one or two calorimeters, the temperature, calorific value and relative density of a gaseous fuel in order to determine the Wobbe index, comparing the Wobbe index value measured with a predefined Wobbe index value for the gaseous fuel and regulating the temperature of the gaseous fuel by means of at least one heat exchanger in order to reach the predefined Wobbe index value. The method may also include using a second gaseous fuel, having a different Wobbe index from the gaseous fuel, or a fuel obtained by mixing the gaseous fuel and the second gaseous fuel, according to arbitrary proportions and variable with time.