AXIAL COMPRESSOR WITH INTER-STAGE CENTRIFUGAL COMPRESSOR

A gas turbine engine (20) comprising a compressor including a first axial rotor (204; 304), a second axial rotor (206; 306) positioned downstream of the first axial rotor (204; 304), and a centrifugal impeller (208; 308) positioned intermediate the first axial rotor (204; 304) and the second axial r...

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Bibliographic Details
Main Authors BINTZ, Matthew, DIBENEDETTO, Enzo
Format Patent
LanguageEnglish
French
German
Published 10.03.2021
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) comprising a compressor including a first axial rotor (204; 304), a second axial rotor (206; 306) positioned downstream of the first axial rotor (204; 304), and a centrifugal impeller (208; 308) positioned intermediate the first axial rotor (204; 304) and the second axial rotor (306; 306) and operably coupled to the first axial rotor (204; 304).
Bibliography:Application Number: EP20180201562