COMPLESSO DI RAFFREDDAMENTO PER CAMICIE DI COMBUSTIONE

A shield (32) is disposed in spaced relationship to the exterior surface of the combustor liner (18) of a gas turbine engine and extends over a plurality of very small holes (28) formed in the combustor liner so as to regulate flow of air to these holes. A portion of the air flowing along the exteri...

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Bibliographische Detailangaben
1. Verfasser:	HOWARD LEWIS FOLTZ
Format:	Patent
Sprache:	ita
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FORCOMBUSTION CHAMBERS, e.g. FIREBRIDGES COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDEDFOR DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS INCOMBUSTION CHAMBERS 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 SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTIONAPPARATUS WEAPONS
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Beschreibung
Zusammenfassung:	A shield (32) is disposed in spaced relationship to the exterior surface of the combustor liner (18) of a gas turbine engine and extends over a plurality of very small holes (28) formed in the combustor liner so as to regulate flow of air to these holes. A portion of the air flowing along the exterior surface of the combustor liner is diverted for reverse flow in the path (44) provided between the shield and the combustor liner. Larger holes (52) are provided in the liner at the point of reversal of the air so that dirt particles in the air, because of the centrifugal force acting thereon, tend to flow through them. A second group of larger holes (56) coiled any remaining dirt particles during a second reversal of air flow. The very small holes are thus protected against being plugged by the particles.