Acoustic treatment method for front fan and dual-flow jet engine of e.g. transport plane, involves arranging cavities on wall near leading edge of blades to reduce amplitude and fluctuations of unsteady pressure in surface of blades

摘要

The method involves arranging cavities (13) on an extrados or intrados wall near a leading edge of blades (12A) of a wheel in a front fan and dual-flow jet engine so as to reduce amplitude and fluctuations of unsteady pressure in surface of the blades. The cavities have a circular section and a diameter lesser than 0.3 millimeters. The wheel is arranged in downstream of another wheel, and forms a stator vane. Independent claims are also included for the following: (1) a broad blade for implementing an acoustic treatment method (2) a jet engine fan comprising a broad blade (3) an aircraft engine comprising a broad blade.