US 12,313,008 B2
Aeronautical propulsion system
Baptiste Dorian Lawniczek, Moissy-Cramayel (FR); Didier René André Escure, Moissy-Cramayel (FR); and Alexandre Thanh Nhan Nguyen, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed on Dec. 15, 2023, as Appl. No. 18/541,066.
Claims priority of application No. 2213619 (FR), filed on Dec. 16, 2022; and application No. 2314106 (FR), filed on Dec. 13, 2023.
Prior Publication US 2024/0200499 A1, Jun. 20, 2024
Int. Cl. F02K 3/06 (2006.01); F01D 5/02 (2006.01); F01D 5/06 (2006.01); F01D 5/14 (2006.01); F01D 5/30 (2006.01); F02C 7/36 (2006.01)
CPC F02C 7/36 (2013.01) [F01D 5/06 (2013.01); F01D 5/14 (2013.01); F01D 5/142 (2013.01); F01D 5/3007 (2013.01); F05D 2220/323 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A propulsion system comprising:
a drive shaft;
a drive turbine comprising a drive turbine stator and a drive turbine rotor, the drive turbine rotor being connected to the drive shaft to drive it in rotation relative to the drive turbine stator about a longitudinal axis, the drive turbine rotor comprising a turbine disk and a plurality of turbine blades;
a fan section comprising a fan rotor and a fan stator, the drive shaft being connected to the fan rotor to drive it in rotation relative to the fan stator about the longitudinal axis;
wherein the turbine disk is centered on the longitudinal axis and has:
an inner surface delimiting a circular bore passing through the turbine disk and centered on the longitudinal axis, the inner surface having an upstream edge and a downstream edge;
an outer surface delimiting a plurality of slots distributed about the longitudinal axis, at least one turbine blade of the plurality of turbine blades comprising a root fixed to the turbine disk in a respective slot of the plurality of slots;
a bore width La which is defined as an axial distance between the upstream edge and the downstream edge of the inner surface; and
a rim radius Rj which is defined as a smallest distance between the longitudinal axis and the outer surface of the turbine disk;
wherein the drive shaft has a limit speed ω which is defined as a highest speed at which the drive shaft is capable of being driven in rotation about the longitudinal axis during the operation of the propulsion system;
wherein the bore width La, the rim radius Rj and the limit speed ω are such that:

OG Complex Work Unit Math
ω is expressed in radians per second;
δ is 0.2424 s2·m−2;
ζ1 is 10;
La and Rj are expressed in meters; and
Uj is expressed in meters per second;
wherein the ratio

OG Complex Work Unit Math
is strictly positive;
wherein the bore width La is comprised in a range from 0.005 to 0.1 meters inclusive, the rim radius Rj is comprised in a range from 0.01 to 0.5 meters inclusive, the limit speed ω is comprised in a range from 209 radians per second to 3,142 radians per second inclusive and Uj is comprised in a range from 100 to 500 m·s−1 inclusive.