GAS TURBINE COMBUSTOR

PROBLEM TO BE SOLVED: To reduce quantity of NOx in combustion gas without deteriorating the reliability of a gas turbine combustor. SOLUTION: In this gas turbine combustor, mixture of steam 41 and fuel gas 43 is injected from a fuel nozzle 7, air 23 for combustion is introduced into a liner 3 and is...

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Bibliographische Detailangaben
Hauptverfasser:	MOMO SATOSHI, INAGE SHINICHI
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 reduce quantity of NOx in combustion gas without deteriorating the reliability of a gas turbine combustor. SOLUTION: In this gas turbine combustor, mixture of steam 41 and fuel gas 43 is injected from a fuel nozzle 7, air 23 for combustion is introduced into a liner 3 and is mixed to burn the fuel gas. The gas turbine combustor is provided with a fuel supply path 19 supplying a mixer 11 with liquid fuel 37 delivered from a first pump 17, and a water supply path 19 supplying the mixer 11 with water 35 delivered from a second pump 13. The fuel supply path 19 and the water supply path 15 are arranged along an outer circumference wall surface of the liner 3 with adhering closely each other, and is provided with decompression means 31, 33 releasing pressure of fluid flowing in each paths at an inlet side of the mixer 11. COPYRIGHT: (C)2009,JPO&INPIT