Methods (200, 555), devices (160, 400) and systems (100) capable of performing a hot restart of a compressor (120) driven by a turbine (110) are provided. The turbine (110) has a high speed shaft (130) and a low speed shaft (140) connected to the compresso...

Systems and methods for controlling the startup of a gas turbine are described. A gas discharge component may be configured to discharge gas from a compressor component associated with the gas turbine. A fuel control component may be configured to control ...

Various embodiments of the present invention reduce the start-up time associated with starting a powerplant machine (100). An embodiment of the present invention provides a method (300) of starting a powerplant machine (100), such as, but not limiting of, ...

Embodiments of the present invention employ a closed loop controls philosophy, which actively controls the starting means (155) of a powerplant machine (100), throughout the start-up process. Here, the present invention may provide a method (500) for adjus...

The method involves driving a set of pumps by an actuator e.g. electric actuator, of a cooling and/or lubricating installation of an aeronautical engine. The pumps are grouped in one device e.g. lubrication group. The lubrication group is driven at constan...

The method involves determining a reference value for operating parameter of a gas turbine, and measuring value for operating parameter during staring phase of the turbine. The measured value and reference value are compared, and presence of the anomaly is...

The generator has an annular case (11) forming a chamber for a pyrotechnic load (12) and composed of unitary load segments (120). The segments have an external dimension lower than the chamber so that passages constituting circulation paths for gas product...