An integrated propulsion system comprising at least two gas turbine engines, at least one fan, and a transmission assembly coupling the at least two gas turbine engines to the at least one fan wherein the at least two gas turbine engines are disposed within a main body of an airframe comprising the main body and a pair of wings, and wherein the number of gas turbine engines is greater than the number of fans.
INTEGRATED AIRCRAFT PROPULSION SYSTEM
2017-03-02
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
The Aircraft/Propulsion Integrated Assessment System
British Library Online Contents | 1992
|European Patent Office | 2020
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