Patent ID: 11933230
Assignee: SAFRAN AIRCRAFT ENGINES
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 0:
1. An aircraft turbomachine having a longitudinal axis, the turbomachine comprising:
a high-pressure (HP) body comprising an HP shaft for connecting an HP compressor rotor to an HP turbine rotor, the HP shaft extending along the longitudinal axis;
a low-pressure (LP) body comprising an LP shaft for connecting an LP compressor rotor to an LP turbine rotor, the LP shaft extending along the longitudinal axis and inside the HP shaft;
a fan connected to a fan shaft; and
an epicyclic reduction gear connecting the LP shaft to the fan shaft,
wherein the LP body comprises:
a first module comprising the LP turbine and the LP shaft, the LP shaft comprising a downstream end coupled to the rotor of the LP turbine;
a second module comprising the LP compressor and a journal secured to the rotor of the LP compressor, the journal being configured to be coupled in rotation to an upstream end of the LP shaft and to be immobilized axially on this end by screwing a nut onto a thread on the shaft; and
a third module comprising an input shaft of the reduction gear, the input shaft comprising an upstream end for coupling to a sun gear of the reduction gear and a downstream end comprising first splines which are oriented parallel to the longitudinal axis and which are configured to be engaged in complementary second splines of said second module, and radially oriented screws being carried by one of the second and third modules and intended to be engaged in the other of the second and third modules in order to axially lock the first and second splines in each other.