Safran Aircraft Engines

Jean-François Endy Bersot

Gilles Alain Charier

Tewfik Boudebiza

Didier Rene Andre Escure

Nicolas Jerome Jean Tantot

Didier René André Escure

Pierre-Alain Jean Philippe Reigner

Thomas Julien Nguyen Van

Stéphane Orcel

Pascal Charles Edouard Coat

Jean Philippe Pierre-Alain Reigner

The invention relates to the rating (S) of a propulsion unit () comprising a main engine () providing main thrust assisted by an auxiliary engine () providing auxiliary thrust, according to the following steps: (i) determining (S) a distribution between the main thrust and the auxiliary thrust so as to obtain the takeoff thrust of the propulsion unit, the auxiliary thrust making a 5% to 65% contribution to the takeoff thrust, (ii) depending on the distribution determined for the takeoff condition, determining (S) distribution between the main thrust and the auxiliary thrust so its to obtain the top of climb thrust of the propulsion unit, the auxiliary thrust making at most 70% contribution to the top of climb thrust, and (iii) rating (S) the propulsion unit () in such a way that the main thrust of the main engine () determined fir the takeoff condition corresponds to the maximum thrust likely to be achieved by the main engine ().

Method for rating a propulsion unit comprising a main engine and an auxiliary engine

Engine comprising a propeller unit with a pair of contrarotating propellers (), a gas generator () supplying a power turbine (), the pair of propellers being rotationally driven by the shaft (A) of the power turbine via a speed reduction gearbox, the axis of rotation (XX) of the pair of propellers not being coaxial with that (YY) of the power turbine, the speed reduction gearbox comprising a differential gearset () and a first stage () comprising a simple gearset connecting the turbine shaft (A) and the differential gearset (), the engine air intake comprising an air intake duct (), the air intake duct () being in the shape of a lobe adjacent to the assembly formed by the simple gearset and the differential gearset ().

Turbine engine with a pair of contrarotating propellers placed upstream of the gas generator

Growing community of inventors

Moissy-Cramayel, France

Jean-François Endy Bersot