Abstract: Aspects of embodiments provide methods and network criticality managers for controlling data traffic in a network. The method may include: obtaining network topology information from a plurality of physical resources used to transfer data traffic in the network; determining priority levels for data traffic in the network; using the network topology information and the determined priority levels to calculate criticality values for physical resources from among the plurality of physical resources, wherein the criticality values for the physical resources indicate the relative importance of the physical resources in the network; and controlling the data traffic in the network based on the calculated criticality values.

Abstract: An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

Abstract: A sump pressurization system comprising an off-board source of pressurized air is provided to supplement pressurized air to a bearing sump arrangement when the operating conditions of the gas turbine engine are such that the on-board pressurized air source, e.g. the compressor of the gas generator, are such that the air pressure generated thereby is insufficient to pressurize a sump pressurization cavity. A gas turbine engine comprising such a sump pressurization system is also provided, as is a corresponding method for operating a gas turbine engine to facilitate reducing leakage of lubrication oil.

Abstract: An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

Abstract: An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

Abstract: A sump pressurization system comprising an off-board source of pressurized air is provided to supplement pressurized air to a bearing sump arrangement when the operating conditions of the gas turbine engine are such that the on-board pressurized air source, e.g. the compressor of the gas generator, are such that the air pressure generated thereby is insufficient to pressurize a sump pressurization cavity. A gas turbine engine comprising such a sump pressurization system is also provided, as is a corresponding method for operating a gas turbine engine to facilitate reducing leakage of lubrication oil.

Abstract: A turbomachine includes a component fixedly constrainable to a baseplate of said turbomachine and an alignment device for regulating the position of the component with respect to the baseplate, wherein the alignment device includes at least a first bolt a second bolt and a third bolt, each bolt including a regulating screw respectively coupled with a threaded through hole in the component, each threaded hole defining a respective alignment axis for said component, each screw having a respective axial end which is susceptible of contacting said baseplate for defining the position of the component along each axis, each bolt including a blocking nut for blocking said regulating screws; the alignment device further includes a fourth fixing screw which is screwable in a threaded hole of the baseplate for fixing said component to the baseplate.

Abstract: An aeroderivative gas turbine including an air intake plenum; a compressor with a compressor air intake in fluid communication with the air intake plenum; a combustor; a high pressure turbine; a power turbine. A forced air-stream generator is arranged in fluid communication with the air intake plenum. A shutter arrangement is provided in a combustion-air flow path, arranged and controlled to close the combustion-air flow path for pressurizing said air intake plenum by means of the forced air-stream generator to a pressure sufficient to cause pressurized air to flow through the aeroderivative air turbine.

Abstract: A gas turbine including: a turbine package, a gas turbine, a ventilation system for cooling the interior of the turbine package, and a lubricating oil circuit. The lubricating oil circuit comprises a lubricating oil pump, a lubricating oil tank, a primary lubricating oil cooler, and a secondary lubricating oil cooler. The secondary lubricating oil cooler is arranged in the turbine package, in a position lower than a rotary shaft of the gas turbine. The ventilation system is arranged and designed such that at least part of a package cooling airflow contacts the secondary lubricating oil cooler to remove heat from the lubricating oil circulating in the secondary lubricating oil cooler.

Abstract: An aeroderivative gas turbine, including a gas generator, a gas generator rotor, a power turbine section, and a slow turning device, wherein said slow turning device is designed and arranged to keep said rotor in rotary motion after turbine shut-down.

Abstract: The invention describes a validation system for a reciprocating fluid machine. The system comprises a base plate or foundation on which at least one frame of the reciprocating fluid machine is removably applied; a first shaft, rotatably coupled with the base plate, to activate the components of the frame; at least one system for generating loads, placed in operative connection with such components and put in rotation by a transmission system through at least one second shaft. The system for generating loads is able to simulate the loads generated by the working fluid on a cylinder of the reciprocating fluid machine.