A turboprop or turboshaft gas turbine engine includes a low pressure turbine drivingly engaged to an output shaft for driving a rotatable load. A low pressure compressor is de-coupled from the low pressure turbine, the low pressure compressor and turbine rotating independently from one another. A high pressure compressor is disposed downstream from the low pressure compressor and is in fluid communication therewith to receive pressurized air therefrom. A high pressure turbine is disposed downstream from the high pressure compressor and is drivingly engaged thereto via a high pressure shaft. The high pressure turbine is disposed upstream from the low pressure turbine and is in fluid communication therewith. An electric motor receives power from a power source, is drivingly engaged to the low pressure compressor, and is operable to drive the low pressure compressor independently from the low pressure turbine, the high pressure compressor and the high pressure turbine.
SPLIT COMPRESSOR GAS TURBINE ENGINE
TURBINE A GAZ A COMPRESSEUR SEPARE
2022-03-08
Patent
Electronic Resource
English
IPC: | F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES |
GAS TURBINE ENGINE ARCHITECTURE WITH SPLIT COMPRESSOR SYSTEM
European Patent Office | 2018
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