Aircraft turbomachine with reduction gearset

Abstract

Aircraft turbomachine (1) with reduction gearset, comprising a first shaft (15) and a second shaft (3) having the one same axis of rotation, the second shaft being rotationally driven by the first shaft via a reduction gearset (7), the first shaft comprising elastically deformable means involving bellows section(s) and being connected to the reduction gearset by a connecting system likewise comprising elastically deformable means involving a hairpin (17) or bellows section(s).

Description

technical field [0001] The invention relates to an aircraft turbine with a reducer. Background technique [0002] Turbines, such as twin-flow turbojet engines, typically include an air intake with a fan whose outlet airflow is divided into an airflow entering the engine and forming a hot or primary flow, and an airflow flowing around the engine and forming a cold or secondary flow. [0003] The engine generally comprises, from upstream to downstream in the direction of airflow, at least one compressor, a combustion chamber, at least one turbine and an exhaust nozzle in which the combustion gases leaving the turbine and forming the main flow are mixed with the secondary flow. Turbines can also be of the "twin body" type, which means that the turbine includes two rotors arranged coaxially. The first body is called the low-pressure body, and the second body is called the high-pressure body. In this case, it is known that an engine has a low-pressure compressor, a high-pressur...

AI Technical Summary

Problems solved by technology

This solution is also too large radially

Images