A combustion module for an aeronautical gas turbine engine, the combustion module having a longitudinal axis, - an inner housing, - an outer housing arranged radially outside the inner housing, - a combustion chamber: -- elongated in an axial direction coaxial with said longitudinal axis, -- in which a mixture of air and fuel can flow from upstream to downstream, and -- disposed between the inner housing and the outer housing, the combustion chamber comprising an inner revolution wall and an outer revolution wall both connected upstream to a chamber bottom wall and both fixed downstream to the inner housing and the outer housing, respectively, and - first stop parts (54, 154) and second stop parts fixed respectively to the outer housing and to the combustion chamber, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs, and, in at least some pairs of said stops, the first stop part (54, 154) being an internal protrusion present on the outer housing, having surfaces (541, 542; 641, 642) respectively axial and radial, characterized in that: - the second stop part has a circumferential outer surface with an axial component, and - an outer radial protrusion, which is radial to the longitudinal axis and against which the radial surface of the first stop part comes into contact, projects locally, opposite the first stop part, from said circumferential outer surface with axial component. - an inner housing, - an outer housing arranged radially outside the inner housing, - a combustion chamber: -- elongated in an axial direction coaxial with said longitudinal axis, -- in which a mixture of air and fuel can flow from upstream to downstream, and -- disposed between the inner housing and the outer housing, the combustion chamber comprising an inner revolution wall and an outer revolution wall both connected upstream to a chamber bottom wall and both fixed downstream to the inner housing and the outer housing, respectively, and -- elongated in an axial direction coaxial with said longitudinal axis, -- in which a mixture of air and fuel can flow from upstream to downstream, and -- disposed between the inner housing and the outer housing, the combustion chamber comprising an inner revolution wall and an outer revolution wall both connected upstream to a chamber bottom wall and both fixed downstream to the inner housing and the outer housing, respectively, and - first stop parts (54, 154) and second stop parts fixed respectively to the outer housing and to the combustion chamber, the first and second stop parts being adapted to come to a substantially axial stop two by two by forming stop pairs, and, in at least some pairs of said stops, the first stop part (54, 154) being an internal protrusion present on the outer housing, having surfaces (541, 542; 641, 642) respectively axial and radial, characterized in that: - the second stop part has a circumferential outer surface with an axial component, and - an outer radial protrusion, which is radial to the longitudinal axis and against which the radial surface of the first stop part comes into contact, projects locally, opposite the first stop part, from said circumferential outer surface with axial component.