Sealing arrangement between two ring-shaped walls of an aircraft engine

A sealing arrangement between two annular walls of an aircraft engine, the two annular walls comprising an inner wall and an outer wall coaxially positioned around an axis, wherein:

• the outer wall comprises an axial end with a cross-section that has the shape of a U having an axis of symmetry arranged parallel to the axis, the U having an opening oriented axially in a first direction;
• and
• the inner wall comprises an axial end with a cross-section that has the shape of a U having an axis of symmetry arranged parallel to the axis, the U having an opening oriented axially in a second direction opposite the first direction;
• the U of the axial end of the outer wall comprising a free annular edge engaged axially in the opening of the axial end of the inner wall, and the U of the cross-section of the axial end of the inner wall comprising a free annular edge engaged axially in the opening of the U of the cross-section of the axial end of the outer wall, so that the inner and outer walls define between them an annular gas passage with an S-shaped axial section,
• wherein at least one seal is mounted in said annular gas passage, the at least one seal including at least one of a labyrinth seal, a brush seal, and a carbon seal and
• wherein in the said annular gas passage, radial gaps are provided (i) between the two free annular edges of the walls and (ii) between the free annular edge of each wall and a surface of the other wall, wherein the gaps are equal.