Method for improving the performance of a bypass turbojet...

Details Method for improving the performance of a bypass turbojet... Method for improving the performance of a bypass turbojet...

F - Mech Eng,Light,Heat,Weapons

02

K

F02K 3/06 (2006.01)

Patent

CA 2702684

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.

Procédé pour améliorer les performances d'un turbomoteur à double flux, dans lequel l'aire de l'orifice annulaire (6) de sortie de flux froid (9) est adaptée à une valeur de référence du taux de détente dudit flux froid (9) comprise entre les valeurs extrêmes dudit taux de détente correspondant respectivement att début et à la fin de la phase de croisière.

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