Distributed cooling for gas turbine engine combustor

A combustor component of a gas turbine engine includes a refractory metal core (RMC) microcircuit (90) in a liner (72,74) for self-regulating a cooling flow. The liner (72,74) includes an inlet (92), first and second divergent islands (94A,94B), a flow separator island (98), first and second feedbac...

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Bibliographische Detailangaben
1. Verfasser:	Cunha, Frank J
Format:	Patent
Sprache:	eng ; fre ; ger
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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Beschreibung
Zusammenfassung:	A combustor component of a gas turbine engine includes a refractory metal core (RMC) microcircuit (90) in a liner (72,74) for self-regulating a cooling flow. The liner (72,74) includes an inlet (92), first and second divergent islands (94A,94B), a flow separator island (98), first and second feedback features (100A,100B) and exit slots (102A,102B).