A turbomachine intended to be mounted on an aircraft, the turbomachine comprising a cascade thrust reverser device and a nacelle with symmetry of revolution defining an axial direction (D A ) and a radial direction (D R ), the nacelle including a thickness along the radial direction (D R ) and a housing extending along the axial direction (D A ) in its thickness to receive a cascade of a cascade thrust reverser device, the thrust reverser device comprising a cascade including first partitions extending in a first direction (D A ), second partitions extending in a second direction (D C ) orthogonal to the first direction (D A ), the second partitions extending between a first and a second end (85 and 86) in a third direction (D R ) secant to a plane comprising the first and second directions (D A and D C ), and at least part of each second partition extending between two first partitions , characterized in that each second partition forms, with reference planes (Pr) parallel to the second direction (D C ) and to the third direction (D R ), a plurality of different angles (α1 to α4) at positions (H1 to H4) distinct from the height (H) of the second partitions separating the first end from the second end of the second partitions , each angle (α1 to α4) being formed between a reference plane (Pr) and the tangent to the second partition taken at the intersection between said corresponding reference plane (Pr) and the second partition , at the position (H1 to H4) of the height (H) of the corresponding second partition , in that the nacelle comprises a perforated wall forming a radially internal wall of the housing and a reflecting wall forming a radially external wall of the housing , the cascade being disposed, when the thrust reversal is not required, in the corresponding housing of the nacelle of the turbomachine with the first partitions extending along the axial direction (D A ) and the radial direction (D R ) and the second partitions extending along the radial direction (D R ) and along a direction orthogonal to the axial direction (D A ) and to the radial direction (D R ), the first direction corresponding to the axial direction (D A ). the thrust reverser device comprising a cascade including first partitions extending in a first direction (D A ), second partitions extending in a second direction (D C ) orthogonal to the first direction (D A ), the second partitions extending between a first and a second end (85 and 86) in a third direction (D R ) secant to a plane comprising the first and second directions (D A and D C ), and at least part of each second partition extending between two first partitions , characterized in that each second partition forms, with reference planes (Pr) parallel to the second direction (D C ) and to the third direction (D R ), a plurality of different angles (α1 to α4) at positions (H1 to H4) distinct from the height (H) of the second partitions separating the first end from the second end of the second partitions , each angle (α1 to α4) being formed between a reference plane (Pr) and the tangent to the second partition taken at the intersection between said corresponding reference plane (Pr) and the second partition , at the position (H1 to H4) of the height (H) of the corresponding second partition , in that the nacelle comprises a perforated wall forming a radially internal wall of the housing and a reflecting wall forming a radially external wall of the housing , the cascade being disposed, when the thrust reversal is not required, in the corresponding housing of the nacelle of the turbomachine with the first partitions extending along the axial direction (D A ) and the radial direction (D R ) and the second partitions extending along the radial direction (D R ) and along a direction orthogonal to the axial direction (D A ) and to the radial direction (D R ), the first direction corresponding to the axial direction (D A ). <EOS>