Combustion chamber with particle separator

A gas turbine engine for an aircraft comprising:

• an engine core comprising a turbine, a compressor, a combustion chamber and a core shaft connecting the turbine to the compressor;
• and
• a fan located upstream of the engine core, the fan comprising a plurality of fan blades,
• wherein the combustion chamber comprises a wall at least partially defining a combustion zone, the wall having an upstream end and a downstream end, the wall having a first surface facing away from the combustion zone and a second surface facing the combustion zone, the wall having at least one effusion cooling aperture extending there-through from the first surface to the second surface, the effusion cooling aperture having an inlet in the first surface and an outlet in the second surface, the first surface having a particle separator at least partially located upstream of the inlet of the effusion cooling aperture, the particle separator projecting away from the first surface and away from the combustion zone, the particle separator having a distal end remote from the inlet of the effusion cooling aperture and a proximal end adjacent to the inlet of the effusion cooling aperture, the particle separator having a maximum height above the first surface at a location spaced from the proximal end, the particle separator increasing in height in a direction from the distal end towards the proximal end to the maximum height,
• the maximum height of the particle separator is equal to or greater than a diameter of the effusion cooling aperture,
• the particle separator overhangs the inlet of the effusion cooling aperture,
• the particle separator has a first portion adjacent the distal end, a second portion adjacent the proximal end and a third portion between the first portion and the second portion, the first portion having a curved surface from the first surface of the wall to the third portion,
• the curved surface of the first portion is an arc of a circle having a radius of four to twelve times the diameter of the effusion cooling aperture,
• the second portion comprises a first curved surface, a second curved surface, and a linear surface between the first curved surface and the second curved surface, the first curved surface, the linear surface and the second curved surface are arranged in series between a junction with the third portion and the first surface of the wall,
• the first curved surface of the second portion is an arc of a circle having a radius of one tenth of the diameter of the effusion cooling aperture, and
• the second curved surface of the second portion is an arc of a circle having a radius of three tenths to twelve tenths of the diameter of the effusion cooling aperture.