PROPULSIVE ASSEMBLY COMPRISING A MAIN ENGINE AND AN AUXILIARY ENGINE

摘要

A propulsion assembly (2) configured to provide a take-off thrust and a climb-up thrust a and comprising: - a main engine (3) configured to provide a main thrust during the take-off regime and the upwind regime having a ratio (QTCHP) between a temperature at the outlet of the high pressure compressor (34) in a climb summit operating condition (TCHP (ToC)) and a temperature at the outlet of the high pressure compressor (34) in takeoff operating condition (TCHP (Tkoff)) is between 0.90 and 1.10, for example between 0.95 and 1.05, and - an auxiliary motor (4), separate from the main engine (3) and configured to provide auxiliary thrust in order to to supplement the main thrust of the main engine (3) during at least the take-off speed.