A gas turbine engine has a core engine incorporating a core engine turbine. A fan rotor is driven by a fan rotor turbine. The fan rotor turbine is in the path of gases downstream from the core engine turbine. A bypass door is moveable from a closed position at which the gases from the core engine turbine pass over the fan rotor turbine, and moveable to a bypass position at which the gases are directed away from the fan rotor turbine. An aircraft is also disclosed.
Gas turbine engine having fan rotor driven by turbine exhaust and with a bypass
2016-05-31
Patent
Electronic Resource
English
Aircraft with gas turbine engine having outer bypass elements removed
European Patent Office | 2018
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