| 摘要 |
A turbojet engine includes a core engine, afterburner, and converging-diverging exhaust nozzle disposed in serial flow communication. A bypass duct surrounds the core engine and afterburner and terminates in flow communication with the exhaust nozzle. The compressor includes first stage fan blades having integral flades at the tips thereof disposed inside the bypass duct. The bypass duct includes a row of variable inlet guide vanes disposed forward of the flades for controlling airflow thereto.
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