FILM COOLING HOLE ARRANGEMENT FOR ACOUSTIC RESONATORS IN GAS TURBINE ENGINES

The present disclosure provides a gas turbine combustor liner (34) comprising an outer surface (38) and an inner surface (36), a plurality of film cooling holes (44) through a thickness of the gas turbine combustor liner (34), and a plurality of resonator boxes (32) affixed to the outer surface (38)...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	Fox Timothy A, Schilp Reinhard
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS
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