GAS TURBINE ENGINE REVERSE-FLOW COMBUSTOR

A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing multiple rows of effusion cooling holes, bounded by cooled effusionless bands to aid in repairability of the co...

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Bibliographische Detailangaben
Hauptverfasser:	MARKARIAN, LORIN, PATEL, BHAWAN B
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BLASTING COMBINED OPERATIONS COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MACHINE TOOLS MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR OTHER WORKING OF METAL PERFORMING OPERATIONS TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine reverse-flow sheet metal combustor for an aero gas turbine engine has a louverless single-piece liner design which includes a plurality of effusion patches, containing multiple rows of effusion cooling holes, bounded by cooled effusionless bands to aid in repairability of the combustor. The cooling of the bands improves the durability of the combustor and provides a method of repair for the combustor. Chambre de combustion à flux inversé en tôle de turbine à gaz comprenant une doublure sans volet faite d'une seule pièce dotée d'une pluralité de zones d'effusion ayant plusieurs rangées d'orifices de refroidissement par effusion, reliées à des zones refroidies sans effusion pour faciliter la réparation de la chambre de combustion. Le refroidissement des zones favorise la durabilité de la chambre de combustion et permet de la réparer.