METHOD AND APPARATUS TO IMPROVE HEAT TRANSFER IN TURBINE SECTION OF GAS TURBINE

PROBLEM TO BE SOLVED: To provide a gas turbine engine system having a combustion section and a turbine section.SOLUTION: A turbine section includes a turbine stage having a plurality of turbine blades coupled to a rotor, and an inner casing circumferentially disposed about the plurality of turbine b...

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Bibliographische Detailangaben
Hauptverfasser:	OZGUR BOZKURT, BALLARD JR HENRY GRADY, BLACK KENNETH DAMON, RADU IOAN DANESCU
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a gas turbine engine system having a combustion section and a turbine section.SOLUTION: A turbine section includes a turbine stage having a plurality of turbine blades coupled to a rotor, and an inner casing circumferentially disposed about the plurality of turbine blades. The turbine section includes an outer casing circumferentially disposed about the inner casing. The inner casing and the outer casing define a cavity comprising a volume configured to facilitate the distribution of air within the cavity to cool an outer surface of the inner casing and an inner surface of the outer casing. The outer casing comprises an air inlet, and the inner casing comprises an air outlet. A flange is provided within the cavity, and the flange flanks the air inlet and a flow guide.