Gas Turbine

The gas turbine comprises a compressor, a combustion chamber (2), a guide vane row (3) and a rotor airfoil row. The guide vane row (3) comprises a plurality of guide vane airfoils comprising a blade (7) and an inner platform (8). The ratio between the pitch (P) and the leading edge diameter (D) of t...

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Bibliographische Detailangaben
Hauptverfasser:	STEPHAN, BRUNO, SOMMER, THOMAS, KRUECKELS, JOERG
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING 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 gas turbine comprises a compressor, a combustion chamber (2), a guide vane row (3) and a rotor airfoil row. The guide vane row (3) comprises a plurality of guide vane airfoils comprising a blade (7) and an inner platform (8). The ratio between the pitch (P) and the leading edge diameter (D) of the guide vane airfoils is between 6.3-7.6 and the ratio between the platform length (L) and the leading edge diameter (D) of the guide vane airfoils is between 4.0-5.5.