Abstract: A method is provided for operating a gas turbine plant including a compressor, which on an inlet side inducts intake air and compresses it, providing compressor exit air on a discharge side. The plant also includes a combustion chamber where fuel is combusted, using compressor exit air, forming a hot gas; and a turbine, where the hot gas is expanded, performing work. The method includes extracting compressed air from the compressor, directing it as cooling air flow into the combustion chamber and/or into the turbine for cooling thermally loaded components. The method also includes controlling at least one cooling air flow, for achieving specific operating targets, using a control element depending on an operating target. A gas turbine plant is also provided having at least one control element for cooling air flow control, and a gas turbine controller which controls the gas turbine plant based on selectable control parameter sets.

Abstract: The invention relates to a surge control method for a gas turbine engine. The method includes providing a gas turbine engine having a compressor, a combustor, downstream of the compressor, with a hot gas path, a turbine downstream of the combustor, with a hot gas path. The method further includes monitoring the gas turbine engine for a potential surge condition, controlling a blow-off flow from the compressor, based on the monitoring for the control purpose of avoiding the surge condition, and directing the blow-off flow to at least one of the hot gas paths so as to bypass at least a portion of the combustor.

Abstract: The invention relates to a surge control method for a gas turbine engine. The method includes providing a gas turbine engine having a compressor, a combustor, downstream of the compressor, with a hot gas path, a turbine downstream of the combustor, with a hot gas path. The method further includes monitoring the gas turbine engine for a potential surge condition, controlling a blow-off flow from the compressor, based on the monitoring for the control purpose of avoiding the surge condition, and directing the blow-off flow to at least one of the hot gas paths so as to bypass at least a portion of the combustor.

Abstract: A method is provided for operating a gas turbine plant including a compressor, which on an inlet side inducts intake air and compresses it, providing compressor exit air on a discharge side. The plant also includes a combustion chamber where fuel is combusted, using compressor exit air, forming a hot gas; and a turbine, where the hot gas is expanded, performing work. The method includes extracting compressed air from the compressor, directing it as cooling air flow into the combustion chamber and/or into the turbine for cooling thermally loaded components. The method also includes controlling at least one cooling air flow, for achieving specific operating targets, using a control element depending on an operating target. A gas turbine plant is also provided having at least one control element for cooling air flow control, and a gas turbine controller which controls the gas turbine plant based on selectable control parameter sets.

Abstract: A high-speed electric machine (10), comprises a rotatably mounted rotor (11) which, separated by an air gap (14), is surrounded concentrically by a stator (12) with two winding overhangs (18,19), and comprises means (20, . . . ,29) for cooling the rotor (11) and stator (12), by means of which a cooling medium, especially cooling air, is sent on a circuit through the rotor (11) and the stator (12), and the heat picked up by the cooling medium or the cooling air in the process is extracted again in a cooler (20).

Abstract: The present invention discloses a rotor (1) for a prime mover or driven machine having a multiplicity of intake passages (5) for rotor cooling air which discharge axially outward. In the region of the axial discharge of the intake passages (5), their inner walls each form funnel-shaped inlet regions (8) which widen outward and open into a common radially extending end face (9). The transitions from the inner walls of the intake passages (5) into the inlet regions (8) and from the inlet regions (8) into the common end face (9) are designed to be smooth in order to avoid sharp transition edges. In this way, the cooling of the rotor (1) can be markedly improved compared with rotors of a similar type of construction.