GAS TURBINE ENGINE

An improved gas turbine engine is disclosed. The engine includes counterrotating first and second turbine rotors without an intervening nozzle. Disclosed also are means for obtaining pitch relative outlet velocity greater than pitch absolute inlet velocity for at least one of the rotors. In one embo...

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Bibliographische Detailangaben
Hauptverfasser:	ROLLIN GEORGE GIFFIN III, DEAN THOMAS LENAHAN
Format:	Patent
Sprache:	eng
Schlagworte:	AEROPLANES AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HELICOPTERS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	An improved gas turbine engine is disclosed. The engine includes counterrotating first and second turbine rotors without an intervening nozzle. Disclosed also are means for obtaining pitch relative outlet velocity greater than pitch absolute inlet velocity for at least one of the rotors. In one embodiment, the reaction of at least one of the rotors is greater than a reference reaction effecting peak efficiency of the one turbine. Advantages include improved overall engine efficiency and decrease in weight, reduced cooling flow and complexity of the engine.