A supersonic turbofan engine includes a fan section having a single-stage fan defining a fan pressure ratio greater than 1.9. The supersonic turbofan engine also includes a core turbine engine defining a core air flowpath. A nacelle at least partially surrounds the fan of the fan section and the core turbine engine. The supersonic turbofan engine defines a bypass ratio, the bypass ratio being greater than or equal to three.
SUPERSONIC TURBOFAN ENGINE
2018-08-02
Patent
Elektronische Ressource
Englisch
PROPELLING NOZZLE FOR A TURBOFAN ENGINE ON A SUPERSONIC AIRCRAFT
Europäisches Patentamt | 2021
|