GAS TURBINE ENGINE WITH INTEGRAL BYPASS DUCT

A gas turbine engine (20) includes an engine core and a bypass duct (40). The engine core includes a compressor section (33), a combustor section (34), a turbine section (35) and a core flowpath (28). The compressor section (33) includes a radial flow compressor rotor (50). The core flowpath (28) ex...

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Bibliographic Details
Main Authors PAULINO, Jose R, JACKSON, Sean R, BINEK, Lawrence A
Format Patent
LanguageEnglish
French
German
Published 22.05.2024
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
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:A gas turbine engine (20) includes an engine core and a bypass duct (40). The engine core includes a compressor section (33), a combustor section (34), a turbine section (35) and a core flowpath (28). The compressor section (33) includes a radial flow compressor rotor (50). The core flowpath (28) extends through the compressor section (33), the combustor section (34) and the turbine section (35) from a core inlet (42) to a core exhaust (44). The bypass duct (40) includes a bypass flowpath (29) that extends outside of the engine core from a bypass inlet (46) to a bypass exhaust (48). The bypass inlet (46) is disposed along the compressor section (33) and fluidly coupled with core flowpath (28).
Bibliography:Application Number: EP20230195213