| 摘要 |
<p>#CMT# #/CMT# The blade (1) has a stacking line (4) extending at a distance ranging between 25 and 50 percent of cord values of an aerodynamic profile integrated root section (5) and an aerodynamic profile integrated end section (6) from a leading edge (2). The root section and the end section are arranged between the leading edge and a trailing edge (3). Cords are extended from the root section toward the end section such that maximum cord value of the end section is equal to or less than 1.6 times of a reference cord of the root section. #CMT# : #/CMT# An independent claim is also included for an anti-torque device comprising a rotor. #CMT#USE : #/CMT# Blade for use in a Fenestron(RTM: shrouded tail rotor) of an anti-torque device (claimed) i.e. rear anti-torque device, of a rotorcraft i.e. helicopter. #CMT#ADVANTAGE : #/CMT# The configuration of the blade allows providing an anti-torque device with maximum thrust gain of order of 4 percentage, reducing static control effort in setting the blade of the rotor and reducing thickness due to large variation of the cords. The configuration of the blade allows reducing interaction noise such as loading noise and dipole noise, between the blade of the rotor and a straightening vane of a stator, and compensating wake deficit observed at the trailing edge to avoid correlation between rotating elements, thus reducing the impact of rotor wake on the vane of the stator and reducing tonal noise. The trailing edge is curved so as to generate phase difference between acoustic waves received by a distant observer, thus reducing the noise perceived by an observer. The configuration of the blade enables improving the performance of the blade, while reducing the peripheral noise of the rotor. The configuration of the blade enables improving anti-torque efficiency of the anti-torque device while avoiding modification of gain in terms of acoustic emission and safety of the anti-torque device. #CMT#DESCRIPTION OF DRAWINGS : #/CMT# The drawing shows a plan view of a blade. 1 : Blade 2 : Leading edge 3 : Trailing edge 4 : Stacking line 5 : Aerodynamic profile integrated root section 6 : Aerodynamic profile integrated end section.</p> |
