US 11,053,800 B2
Turbine rotor disk blade having a foot of curvilinear shape
Bruno Marc-Etienne Loisel, Moissy-Cramayel (FR); Carine Thuy-Huong Pragassam, Moissy-Cramayel (FR); Nicolas Marc Florent, Moissy-Cramayel (FR); and Marion France Chambre, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
Filed on Sep. 12, 2019, as Appl. No. 16/568,805.
Claims priority of application No. 18 58324 (FR), filed on Sep. 14, 2018.
Prior Publication US 2020/0141243 A1, May 7, 2020
Int. Cl. F01D 5/12 (2006.01); F01D 5/30 (2006.01)
CPC F01D 5/12 (2013.01) [F01D 5/30 (2013.01); F05D 2220/30 (2013.01)] 11 Claims
OG exemplary drawing
 
1. A rotor blade for a rotor disk of a turbine of a turbomachine comprising, in a radial direction from inside to outside:
a blade foot root;
a support;
a platform; and
a rotor vane,
wherein the root is connected to the support by a neck,
wherein the neck has a curvilinear profile defining, in a section in a plane perpendicular to the radial direction, a dished shape,
wherein a section of the neck overlaps at least 75% of a section of the rotor vane, as a projection of the sections of the neck and of the rotor vane in a plane perpendicular to the radial direction, in an area where the section of the rotor vane joins the platform, and
wherein, in the projection of the sections of the neck and of the rotor vane in the plane perpendicular to the radial direction in the area where the section of the rotor vane joins the platform, a leading edge of the rotor vane is further upstream than an upstream end of the neck in an axial direction and a trailing edge of the rotor vane is further downstream of a downstream end of the neck in the axial direction.