GAS TURBINE COMBUSTOR

PROBLEM TO BE SOLVED: To provide a gas turbine combustor that suppresses generation of combustion oscillation to improve reliability.SOLUTION: A gas turbine combustor includes a combustion chamber into which fuel and air are supplied, an air hole plate located on an upstream side wall surface of the...

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Bibliographische Detailangaben
Hauptverfasser:	YOSHIDA SHOHEI, AKIYAMA KYOTA, MOMO SATOSHI, ASAI TOMOHIRO
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:	PROBLEM TO BE SOLVED: To provide a gas turbine combustor that suppresses generation of combustion oscillation to improve reliability.SOLUTION: A gas turbine combustor includes a combustion chamber into which fuel and air are supplied, an air hole plate located on an upstream side wall surface of the combustion chamber with a plurality of air holes formed in concentric circular rows, and fuel nozzles disposed at an upstream side of each air hole of the air hole plate. In at least one row of the air holes formed in the concentric circular rows on the air hole plate, distances between leading ends of the fuel nozzles and a combustion chamber side surface of the air hole plate are different in a circumferential direction.