Variable power nozzle ejector for turbine system

A gas turbine engine system (200). The system (200) includes a compressor (12) with a first compressor stage (20) and a second compressor stage (24), a turbine (14) with a first turbine stage (21) and a second turbine stage (28), a first flow path (22) connecting the first compressor stage (20) and...

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Bibliographische Detailangaben
1. Verfasser:	WOLFE CHRISTOPHER E.,BEADIE DOUGLAS F.,WHALING KENNETH N.,BALL DAVID W.,MCGOVERN KEVIN T.,ELURIPATIRAVI PRAVEEN,SAMUDRALA OMPRAKASH
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A gas turbine engine system (200). The system (200) includes a compressor (12) with a first compressor stage (20) and a second compressor stage (24), a turbine (14) with a first turbine stage (21) and a second turbine stage (28), a first flow path (22) connecting the first compressor stage (20) and the first turbine stage (21), a second flow path (26) connecting the second compressor stage (24) and the second turbine stage (28), a crossover flow path (31) connecting the first flow path (22) and the second flow path (26), and an ejector (100) positioned about the crossover flow path (31) and the first flow path (22). The ejector (100) may be a variable motive nozzle ejector (100).