Combustor dilution hole

A turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor line...

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Bibliographische Detailangaben
Hauptverfasser:	Vukanti, Perumallu, Lakshmanan, Varun, Gandikota, Gurunath, Danis, Allen M, Benjamin, Michael A
Format:	Patent
Sprache:	eng
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 turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor liner is joined to an annular combustor dome via front portion and defines a chamber and a nozzle is mounted within the annular combustor dome and is configured to inject fuel into a plurality of swirlers. At least one or more dilution openings is circumferentially distributed around the liner such that a region is fluidly connected through the annular combustor liner to the chamber. Each one of the pluralities of dilution openings includes an opening and a radial support wall that is positioned aft of the opening such that the radial support wall extends into the chamber.