Combustion section with a casing shielding

An assembly for a gas turbine, the assembly comprising a rotor axis, a compressor section, and a combustion section, the combustion section comprising:

• an upstream side and a downstream side;
• an annular combustion, chamber;
• a burner arrangement upstream of the annular combustion, chamber;
• an annular compressor diffusor downstream of the compressor section and having an annular inner diffusor wall and an annular outer diffusor wall, the annular outer diffuser wall having a wall end at a downstream side of the annular outer diffusor wall;
• an annular combustion casing having an outer section wall extending along the rotor axis and arranged radially outward relative to the annular combustion chamber, an upstream section wall extending along a radial direction and arranged upstream relative to the annular combustion chamber, and an inner section wall extending along the rotor axis and arranged between the burner arrangement and the compressor diffusor, wherein the outer diffusor wall the inner section wall in an axial direction;
• and
• a shielding attached to the inner section wall on a radially inner side of the inner section wall facing the rotor axis, wherein a free space is defined between the shielding and the radially inner side of the inner section wall along at least half of an axial length of the inner section wall, wherein the wall end of the annular outer diffuser wall is arranged axially between an upstream end of the shielding and an axial midpoint of the shielding.