A propulsion unit for an aircraft is provided. The propulsion unit includes a main engine that supplies main thrust during a takeoff operating condition and a top of climb operating condition, and an auxiliary engine, distinct from the main engine, that supplies auxiliary thrust to complete the main thrust of the main engine during the takeoff operating condition. The main engine includes a high-pressure compressor. The main engine is dimensioned taking into account the thrust of the auxiliary engine in the takeoff operating condition, in such a manner that a temperature ratio of the high-pressure compressor, corresponding to the ratio between an outlet temperature of the high-pressure compressor of the main engine in the top of climb operating condition and an outlet temperature of the high-pressure compressor of the main engine in the takeoff operating condition, is between 0.90 and 1.10.
PROPULSION UNIT COMPRISING A MAIN ENGINE AND AN AUXILIARY ENGINE
2018-11-15
Patent
Electronic Resource
English
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