Multihole patch for combustor liner of a gas turbine engine

A liner (34) for a combustor (16) of a gas turbine engine (10), including a shell (34) having a first end (46) adjacent to an upstream end of the combustor (16) and a second end (60) adjacent to a downstream end of the combustor (16), wherein at least one discrete region (72) is subject to distress...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	LIND, DAVID ALBIN, MILLS, BRUCE ERNEST, HOLMES, JAMES PATRICK, MOERTLE, GEORGE ERIC, HARRIS, TARIQ KAY
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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