Cooling the rotor of an axial gasturbine

The multi-stage turbine (1) drives a compressor (10) mounted on a common shaft (13). The shaft part between turbine and compressor is a drum (14) enclosed by a cover (15) forming a ring channel (20) containing a labyrinth seal (21) which seals against the cover (15). The drum cover together with the...

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Bibliographische Detailangaben
Hauptverfasser:	MARMILIC, ROBERT, WAELCHLI, RENE
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The multi-stage turbine (1) drives a compressor (10) mounted on a common shaft (13). The shaft part between turbine and compressor is a drum (14) enclosed by a cover (15) forming a ring channel (20) containing a labyrinth seal (21) which seals against the cover (15). The drum cover together with the end side (18) of the turbine rotor (3) define a radially wheel side chamber (19). At least one separate pipe (22) leading the rotor cooling air from the compressor to the end side of the rotor is connected to the wheel side chamber by at least two vortex nozzles (23). Cooling devices (24) are provided from the rotor and rotor vane rim. The entire cooling air on the rotor side for the turbine is removed from the compressor at the compressor outlet.