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The invention relates to a vane segment (10) for a gas turbine, in particular aircraft gas turbine, comprising at least one radially outer band (14) and a radially inner shroud (12) extending along a respective circular arc and together form a ring portion, in the radial direction (RR) between the outer shroud (14) and said inner band (12) a plurality of vanes (16, 16a) in the circumferential direction (UR) are arranged side by side, with the inner band (12) and said outer band (14) material-locking connected are in particular connected in one piece, wherein the outer band (14) in an axial longitudinal direction (AR) an axially forward end wall member (20) and an axially rearward end wall member (22) such that said outer band (14) and the two end walls ( 20, 22) form in longitudinal section a trough-like profile, wherein the outer shroud (14) for each vane (16, 16a) of an associated Verstar is formed kung rib (32, 32a) extending between the two end walls (20, 22). According to the invention it is proposed that at the rear end wall at at least one vane (16a) (22) at least two adjacently disposed securing ribs (34, 36) are formed, wherein a through the two securing ribs (34, 36) in the circumferential direction (UR) of limited space (40) is formed radially outside to radially inside tapered.