DUAL-USE AIR TURBINE SYSTEM FOR A GAS TURBINE ENGINE

A dual-use air turbine system (40) for a gas turbine engine of an aircraft is provided. The dual-use air turbine system includes a variable area air turbine (42) mechanically linked to a spool of the gas turbine engine through a multi-speed gear set (44). The dual-use air turbine system also include...

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Bibliographische Detailangaben
1. Verfasser:	Feulner, Matthew R
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING PARACHUTES PERFORMING OPERATIONS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	A dual-use air turbine system (40) for a gas turbine engine of an aircraft is provided. The dual-use air turbine system includes a variable area air turbine (42) mechanically linked to a spool of the gas turbine engine through a multi-speed gear set (44). The dual-use air turbine system also includes a plurality of valves (60; 62; 64; 66; 68) in pneumatic ducting (52) operable to direct an engine start air flow (54) through an inlet (58) of the variable area air turbine (42) and drive rotation of the spool during an engine start mode of operation. The valves are further operable to direct an engine bleed air flow (70) from a compressor section (24) of the gas turbine engine through the inlet of the variable area air turbine and drive rotation of the spool during an environmental control system active mode of operation.