Combustor and gas turbine

To achieve a reduction in waste heat loss of a fuel with improved efficiency in arrangement of a plurality of cavities, or manifold spaces. A multi-stage combustor includes a combustor liner configured to define a combustion chamber therein, a plurality of fuel nozzles configured to inject a fuel, a...

Ausführliche Beschreibung

Bibliographische Detailangaben

Hauptverfasser:	Yagi, Nobuo, Dodo, Satoshi, Karishuku, Mitsuhiro
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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