FILM COOLING HOLE IN GAS TURBINE COMPONENTS

A film-cooling hole of gas turbine components to be cooled has an inflow section which has a constant throughflow cross section and which is adjoined by a diffuser section which has a varying throughflow cross section. The widening of the diffuser region occurs only in the direction which is perpend...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	BECK, Thomas, DAHLKE, Stefan, HOHENSTEIN, Sebastian, DIETRICH, Jens
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A film-cooling hole of gas turbine components to be cooled has an inflow section which has a constant throughflow cross section and which is adjoined by a diffuser section which has a varying throughflow cross section. The widening of the diffuser region occurs only in the direction which is perpendicular to the flow direction of the relatively hot medium.