To provide an aviation gas turbine system capable of obtaining sufficient output even during flight at high altitudes with low air density.
This gas turbine engine assembly 10 comprises a propelling gas turbine engine 11 having a fan assembly 14 and a core engine assembly 13 located downstream of the fan assembly. The core engine comprises a booster compressor 102, a high pressure compressor 22, a high pressure turbine assembly 24, a booster turbine assembly 104, a low pressure turbine assembly 16 and a power generating auxiliary engine 12 coupled together in serial-flow arrangement such that the booster turbine is rotatably coupled to a booster fan. The auxiliary engine is coupled in communication with the core engine of the propelling gas turbine engine such that a part of air flow 40 entering the propelling engine is extracted for use by the auxiliary engine.
TRUCO JOHN B
| JPH0719068A | 1995-01-20 |
Hirokazu Ogura
Toshihisa Kurokawa