Vane segment with radial assurance

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) in the circumferential direction (UR) are arranged side by side, with the inner band (12) and said outer band (14) material positively connected, in particular are integrally connected, wherein the outer band (14) in an axial longitudinal direction (AR) an axially forward end wall member (22) and an axially rearward end wall element (22), such that the outer band (14) and the two end walls (22 , 24) form a trough-like profile in the longitudinal section, where (on the axially rear end wall 24) SHEET IFRS at least one radial locking element (26) s, which is arranged to the guide vane segment (10) in radial direction (RR) relative to a surrounding housing (28, 30) to secure, wherein the radial locking element (26) is formed as a projection having a support portion (27) to is arranged on a corresponding counterpart (30) on the housing (28) to be supported. According to the invention it is proposed that the support section (26) has a support surface (32) lies in a plane whose normal vector the vector components in the circumferential direction (UR) and in the axial direction (AR) and / or in radial direction (RR) has.