Abstract: An igniter plug for an aircraft turbomachine includes an external electrode, an internal electrode, as well as a semiconducting body arranged between the external electrode and the internal electrode and set back from these electrodes so as to define an electrical arc forming cavity, the bottom of which is formed by an axial end surface of the semiconducting body. The free end of the external electrode is equipped with at least one scoop for discharging possible fuel residues present in the cavity.

Abstract: The invention relates to an igniter plug (30) for an aircraft turbomachine, comprising an external electrode (34), an internal electrode (36), as well as a semiconducting body (38) arranged between the external electrode and the internal electrode and set back from these electrodes so as to define an electrical arc forming cavity (40), the bottom of which is formed by an axial end surface (42) of the semiconducting body. According to the invention, the end of the external electrode (34) is equipped with at least one scoop (44) for discharging possible fuel residues present in the cavity (40).

Abstract: An annular wall for the combustion chamber of a turbomachine has a cold side and a hot side, said wall being provided with a plurality of primary holes and a plurality of dilution holes distributed in circumferential rows, together with a plurality of cooling orifices that are distributed in a plurality of circumferential rows that are spaced apart axially from one another, the number of cooling orifices being identical in each row thereof, and the wall further including bores disposed immediately downstream from the primary holes and from the dilution holes and distributed in circumferential rows, the bores in any one row presenting a substantially identical diameter, being spaced apart at a pitch that is constant, and presenting intrinsic characteristics that are different from the intrinsic characteristics of the cooling orifices of the adjacent rows.

Abstract: The invention relates to the field of turbomachines and concerns a combustion chamber (4) for which the dilution supply is optimised. The invention relates more particularly to optimisation of the position of the dilution holes (30a, 30b) present on the walls (7a, 7b) of the combustion chamber.