METHOD FOR IMPROVING THE PERFORMANCE OF A BYPASS TURBOJET ENGINE AND TURBOJET ENGINE USING SAID METHOD

摘要

Method for improving the performance of a bypass turbojet engine, wherein the area of the annular outlet orifice (6) for the cold stream (9) is tailored to suit a reference value of the expansion ratio of said cold stream (9) which ranges between the extreme values of said expansion ratio corresponding respectively to the start and end of the phase of cruising flight.