US 11,834,165 B2
Method for improving the aerodynamic behavior of rotorcraft blades during hovering flight by moving the leading edge of the aerodynamic profiles of these blades
Manousos Kelaidis, Marseilles (FR)
Assigned to AIRBUS HELICOPTERS, Marignane (FR)
Filed by AIRBUS HELICOPTERS, Marignane (FR)
Filed on Sep. 17, 2021, as Appl. No. 17/477,935.
Claims priority of application No. 2010434 (FR), filed on Oct. 13, 2020.
Prior Publication US 2022/0111955 A1, Apr. 14, 2022
Int. Cl. B64C 27/467 (2006.01); B23P 15/28 (2006.01)
CPC B64C 27/467 (2013.01) [B23P 15/28 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method for manufacturing a blade, the blade extending in a longitudinal direction spanwise from a first end to a second end and in a transverse direction from a leading edge towards a trailing edge, the blade comprising successive transverse sections, the transverse sections being defined by aerodynamic profiles, each of the aerodynamic profiles being defined by two half-profiles including an upper surface half-profile and a lower surface half-profile, the two half-profiles each comprising a leading edge section, an intermediate section and a trailing edge section, the first end being intended to be connected to a hub of a rotor, the second end being intended to be free,
wherein the method comprises the following steps:
defining a straight-line segment connecting the leading edge and the trailing edge of existing aerodynamic profiles;
shifting only the leading edge of the existing aerodynamic profiles situated in a spanwise end zone of the blade comprising the second end, the shift being carried out from the upper surface half-profiles towards the lower surface half-profiles over a first distance d1 perpendicular to the straight-line segment;
modifying the leading edge sections of the two half-profiles of the existing aerodynamic profiles connecting the leading edge to the intermediate sections of the two half-profiles in the spanwise end zone for obtaining modified aerodynamic profiles; and
manufacturing the blade according to the modified aerodynamic profiles.