Heterogeneous distribution of leading edge gaps

Abstract

Heterogeneous distribution of leading edge slots. The present invention relates to a row of turbomachine blades (120a, 120b, 130a, 130b) arranged around a central axis (X). This row of turbomachine blades (120a, 120b, 130a, 130b) comprises a first set of blades (120a, 130a) each with a set of leading edge slots (200), as well as at least a second set of blades (120b, 130b) none of which has a set of leading edge slots (200) substantially identical to the set of leading edge slots (200) of each blade (120a, 130a) of the first set of blades (120a, 130a). We also obtain a heterogeneous distribution of the leading edge slots (200) on the different blades (120a, 120b, 130a, 130b) of this row. Figure for the abbreviation: Fig. 3C.

Claims

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11. upstream of this one, another row of blades (110), arranged rotating around the central axis (X). Propulsive blower (100) according to claim 5, wherein at least some blades (120a, 130a) of said first set of blades are located downstream of a descending sector of the other row of blades (110). Propeller (10) comprising the propulsive blower according to claim 5 or 6. Propeller (10) according to claim 7, further comprising a support (50) disposed downstream of the first row of blades (110). Propeller (10) according to claim 8, wherein the propulsive fan (100) is an unfaired propulsive fan, and said second set of blades (120b) of the second row of blades (120a,120b) comprises at least two blades (120b), each of which is devoid of slots along its entire leading edge (BA), disposed adjacent to the support (50) on one side and on the other side of the support (50) in a circumferential direction around the central axis (X). Gas turbine engine (11) comprising the row of blades (130a, 130b) according to any one of claims 1 to 4 as a row of inlet guide blades. Aircraft (1) comprising the propulsion unit (10) according to any one of claims 1 to 9 and / or the gas turbine engine (11) according to claim 10. / [Fig. 2]

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