COMBUSTION SYSTEMS

A combustor for a gas turbine engine includes an inner combustor wall (104) and an outer combustor wall (106) radially outboard of the inner combustor wall (104). The inner and outer combustor walls define a combustion space therebetween with an upstream inlet (110) and a downstream outlet (112). A...

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Bibliographische Detailangaben
1. Verfasser:	PROCIW, Lev Alexander
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBUSTION APPARATUS COMBUSTION PROCESSES GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING LIGHTING MECHANICAL ENGINEERING WEAPONS
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Zusammenfassung:	A combustor for a gas turbine engine includes an inner combustor wall (104) and an outer combustor wall (106) radially outboard of the inner combustor wall (104). The inner and outer combustor walls define a combustion space therebetween with an upstream inlet (110) and a downstream outlet (112). A combustor dome (102) connects between inner and outer combustor walls at the upstream inlet of the combustion space. The combustor dome (102) includes a plurality of circumferentially spaced apart nozzles and a plurality of tiles (134) mounted to the combustor dome to fluidly separate a downstream side of the combustor dome (102) from an upstream side of the combustor dome (102).