Abstract: An igniter plug arrangement is disclosed. The arrangement includes an igniter plug of the semiconductor in shell type, a duct secured to a combustion chamber of a gas turbine engine, a floating sleeve via which the igniter plug is mounted in the duct, and a system for guiding air to cool the semiconductor of the igniter plug. The shell and the semiconductor define, at their combustion-chamber end, an annular igniter plug cavity. The shell includes orifices in the region of the igniter plug annular cavity that communicate with the annular cavity of the sleeve and orifices on its planar surface.

Abstract: A method involved operating a combined-cycle power plant (10), which has a gas turbine (11) with a compressor (12) and a turbine (13), a heat recovery steam generator (17) which is connected downstream to the gas turbine (11) and is for producing steam in a water/steam cycle, and also at least one once-through cooler (21), through which flows compressed air which is compressed in the compressor (12) and intended for cooling the gas turbine (11), and, cooling down, converts feed-water (24) which is fed from the heat recovery steam generator (17) into steam, and discharges the steam to the heat recovery steam generator (17). Making the operation more flexible is achieved, without lowering the load of the gas turbine (11), by the combined-cycle power plant (10) being switched between a first operating mode, in which only the gas turbine cycle is used for power generation, and a second operating mode, in which the gas turbine cycle and the water/steam cycle are used for power generation.

Abstract: A nozzle section of a gas turbine engine includes a regulator system in fluid communication with a secondary flow duct and a tertiary flow duct to selectively regulate communication of secondary airflow into the tertiary flow duct.

Abstract: A gas turbine system includes a combustion chamber (2), a turbine (3), a radially inward and/or radially outward axial gap (4; 16, 17) between the combustion chamber (2) and the turbine (3), at which gap inner and/or outer combustion chamber walls (7, 8) and inner and/or outer turbine walls (11, 12) end, and a cooling gas supply (5), which via the gap (4; 16, 17) introduces a cooling gas into the turbine gas path (13) and/or into the combustion chamber gas path (9). An end section (21, 22, 23, 24) of the respective turbine wall (11, 12) and/or of the respective chamber wall (7, 8) adjoining the gap (4; 16, 17) is radially inwardly and/or radially outwardly, alternatingly formed.

Abstract: A gas turbine equipped with a burner, which has an axial swirler for generating turbulence in a flow of comburent air, a secondary supply line of fuel gas, a main supply line of fuel gas arranged concentrically around the secondary line, and a pilot line of fuel gas. Accordingly, the burner is ignited by firing a spark and feeding, towards the spark, comburent air and fuel gas which is synthesis gas.

Abstract: A twin-spool gas turbine engine including a high-pressure rotor and a low-pressure rotor, which rotors are mounted in bearings supported by an intermediate casing, at least one accessory gear box, and a drive device which drives radial and coaxial shafts for transmitting movement to the accessory gear box is disclosed. The drive device includes a high-pressure drive gear driving one of the radial shafts and connected to the high-pressure rotor and a low-pressure drive gear connected to the low-pressure rotor upstream of the high-pressure drive gear and driving the other of the radial shafts. The low-pressure drive gear is supported in the intermediate casing by an axial-positioning bearing.

Abstract: A mixer having a unitary construction is disclosed comprising an annular housing having an axis and at least a first swirler having a plurality of vanes arranged circumferentially around the axis such that circumferentially adjacent vanes form at least one flow passage that is oriented at least partially in an axial direction with respect to the axis. In another exemplary embodiment, a mixer having a unitary construction is disclosed comprising a swirler having a plurality of radial vanes arranged circumferentially around the axis and oriented at least partially in a radial direction.