| 摘要 |
A gas turbine engine (10, fig 1) comprises, a fan (12, fig 1), a core engine 23 in flow relationship with, and located downstream from, the fan 12, an annular bypass duct 36 surrounding the core engine 23 and also being in flow relationship with, and located downstream from, the fan 12, and at least one pulse detonation tube 102 located radially outwardly of the core engine 23. The engine may comprise a plurality of pulse detonation tubes 102 circumferentially spaced within the bypass duct 36 and downstream of the fan 12. Airflow from the bypass duct 36 into the tube(s) 102 may be controlled by a rotary valve 124 which may comprise a rotor disk 126 comprising at least one opening 128 and be driven by electric, hydraulic or air motor 132. |
