Gas turbine annular combustor arrangement

The invention relates to a combustor arrangement (1), the combustor arrangement (1) being annular and being arranged about an axis, the axis defining an axial direction (A), comprising an annular housing (2) to house a plurality of burners (3) and an annular combustion chamber (4), the plurality of burners (3) arranged circumferentially about the axis inside the annular housing (2), wherein an annular space (5) is defined between the housing (2), the burners (3) and the annular combustion chamber (4), the annular space (5) arranged to guide a compressed fluid (6). Further comprising a plurality of stiffening plates (10), each arranged within the annular housing (2), wherein two adjacent ones of the burners (3) are separated by one of the stiffening plates (10). Besides, the combustor arrangement (1) comprises a combustor separating wall arrangement (15) to separate the annular space (5) from the annular combustion chamber (4) and to provide openings (16) for the plurality of burners (3). Further, the stiffeni