Variable bypass ratio augmented gas turbine engine

A variable bypass ratio augmented gas turbine engine system for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines...

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Bibliographic Details
Main Author PAULINO JOSE R
Format Patent
LanguageEnglish
Published 30.09.2014
Subjects
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
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:A variable bypass ratio augmented gas turbine engine system for a UAV with a high pressure ratio gas turbine engine used for low power operation such as loiter speed and a low pressure ratio gas turbine engine used for high power operation. A power turbine receives hot gas flows from the two engines to drive an output shaft. At low power operation, only the high pressure ratio engine is operated. At high power operation, both engines are operated where the exhaust from the high pressure ratio engine is mixed with bleed off air form the second compressor to produce a second hot gas flow in a second combustor to drive the second turbine. The remaining compressed air from the second compressor is passed into a third combustor to produce a third hot gas flow that then flows into the power turbine.
Bibliography:Application Number: US201113251946