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...

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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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Beschreibung
Zusammenfassung:	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 from impingement of hot gases, a plurality of cooling slots (56) formed in the shell (34) through which air flows for providing a cooling film along a hot side (58) of the shell (34), and a group (74) of cooling holes (82,84) formed in the shell (34) in the discrete region (72) to augment the cooling film and provide convective bore cooling to the discrete region (72).