ROTATING FUEL NOZZLE FOR GAS TURBINE

PURPOSE: A rotating fuel nozzle for a gas turbine is provided to sequentially supply fuel by ignition, acceleration, and fixation steps through each orifice using a fuel injection structure formed in a step shape. CONSTITUTION: A rotating fuel nozzle for a gas turbine comprises a fuel injection hole...

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Bibliographische Detailangaben
Hauptverfasser:	MIN, SEONG GI, KIM, YOU IL, YOU, GYONG WON, LEE, DONG HUN
Format:	Patent
Sprache:	eng ; kor
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 SUPPLYING COMBUSTION ENGINES IN GENERAL, WITH COMBUSTIBLEMIXTURES OR CONSTITUENTS THEREOF WEAPONS
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Beschreibung
Zusammenfassung:	PURPOSE: A rotating fuel nozzle for a gas turbine is provided to sequentially supply fuel by ignition, acceleration, and fixation steps through each orifice using a fuel injection structure formed in a step shape. CONSTITUTION: A rotating fuel nozzle for a gas turbine comprises a fuel injection hole(240), orifices(301,302,303), a combustion chamber(250), a slope(333), and a closed drum structure(350). The fuel injection hole is orifice. The combustion chamber is located outside a rotary shaft(200). The slope of the closed drum structure of the rotary shaft consists of steps. The orifice is formed on the surface of the slope. The closed drum structure forms walls(331,332). The wall blocks fuel from final orifice from flowing. The orifice is formed perpendicular to the rotary shaft. The orifices have a circular cross section and are arranged in parallel to each other.