of hot gas directed to the stator in correspondence of the gaps 4 and 8 in fact seals 4 and 8 cannot be completely tight due to relative movements of gas turbine components such as turbine and combustor for example during start up operations and or different operative regimes of the gas turbine as a consequence of this purge air p usually coming from the compressor end leaks through gaps 4 and 8 and mixes with the flow f of hot air this also avoids hot gas entering into the gaps for the reasons explained above additionally leakage purge air also fulfils a cooling function associated to the vane platform 3 according to an aspect of the invention gas turbine 1 further comprises a plurality of cooling ducts 5 which are located upstream the inner gap 4 relative to the flow of hot gas indicated with arrow f and within the inner wall 21 of combustor 2 alternatively or additionally gas turbine 1 may also comprise a plurality of cooling ducts 9 which are located upstream outer gap 9 and within the outer wall 22 of the combustor 2 according to a preferred and non limiting example cooling ducts 5 and 9 have a circular cross section preferably the cooling ducts are arranged within said inner and or outer combustor walls 21 22 such to fluidically connect the combustor 2 with a portion 12 which is defined between the combustor walls 21 and 22 and a combustor liner not shown advantageously the cooling air exiting the cooling.