Axially separate rotor end piece

A rotor end piece ( 1 ) for a rotor of a thermal turbomachine, having at least one circumferential slot ( 3 ) in which press blades, intermediate pieces and two end blades ( 4 ), between which a residual gap is formed, are fitted, the rotor end piece ( 1 ) having two end piece halves ( 9, 9 ) and a...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	RUBISCHON KURT, BACHOFNER RENE, KAPPIS WOLFGANG
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A rotor end piece ( 1 ) for a rotor of a thermal turbomachine, having at least one circumferential slot ( 3 ) in which press blades, intermediate pieces and two end blades ( 4 ), between which a residual gap is formed, are fitted, the rotor end piece ( 1 ) having two end piece halves ( 9, 9 ) and a wedge ( 7 ), is characterized in that a clip ( 8 ) is arranged in the residual gap, this clip ( 8 ) absorbing the forces of the two end piece halves ( 9, 9 ) and two shim halves ( 5, 6 ) arranged between the end piece halves ( 9, 9 ) and restrained with the wedge ( 7 ). As a result, the disadvantages of the prior art are avoided and a rotor end piece is provided which exerts no axial forces on the rotor and no forces on adjacent blades in the circumferential direction, so that an occurrence of disturbing rotor vibrations and jamming of adjacent blades is effectively avoided.