SYSTEM AND METHOD FOR RAPID TURBINE DECELERATION

PROBLEM TO BE SOLVED: To provide a gas turbine engine system for turbine deceleration during shutdown procedures.SOLUTION: The gas turbine engine system (100) includes a rotor (170) extending through a turbine (160), a generator (180) engaged with the rotor (170), and a starting system (210) in comm...

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Bibliographische Detailangaben
Hauptverfasser:	SNIDER DAVID AUGUST, MEMMER JOHN DAVID
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 INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 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 for turbine deceleration during shutdown procedures.SOLUTION: The gas turbine engine system (100) includes a rotor (170) extending through a turbine (160), a generator (180) engaged with the rotor (170), and a starting system (210) in communication with the rotor (170). The starting system (210) reverses the operation of the generator (180) so as to apply torque to the rotor (170) during the shutdown procedures.