A gas turbine for power plant; the gas turbine comprising: - at least a combustor, preferably a plurality of can combustors; - a turbine downstream the combustor; wherein - the combustor comprises a downstream end, preferably a picture frame for each can combustor, facing the turbine and provided with an inner groove; - the turbine comprises a plurality of a first stator vanes; each first stator vane comprising an inner platform provided with a tooth projecting in part inside the inner groove; wherein a plurality of seals are provided housed in the inner grooves of the combustor downstream end and are configured for cooperating with the vane teeth for sealing each can combustor to turbine interface; wherein at least a seal is a honeycomb seal device, the honeycomb seal device being characterized in that the honeycomb seal device is an assembly comprising a honeycomb body made of a plurality or radial cells and a shield body covering at least the part of the honeycomb body cooperating with the vane tooth; wherein each groove and the honeycomb body have a annular extent; the honeycomb body comprises a front face directed towards the turbine, an opposite back face facing the bottom of the groove, an inner face facing the inner surface of the groove and an outer face facing the outer surface of the groove; the shield body covering the front face and part of the inner face and the outer face of the honeycomb body; wherein the honeycomb body discloses a T-cross section wherein an upstream portion has a radial extent higher than a downstream portion; the shield body covering either the entire inner face and the outer face corresponding to the downstream portion of the honeycomb body, or only a part of the inner face and the outer face corresponding to the downstream portion of the honeycomb body. - at least a combustor, preferably a plurality of can combustors; - a turbine downstream the combustor; - the combustor comprises a downstream end, preferably a picture frame for each can combustor, facing the turbine and provided with an inner groove; - the turbine comprises a plurality of a first stator vanes; each first stator vane comprising an inner platform provided with a tooth projecting in part inside the inner groove; a plurality of seals are provided housed in the inner grooves of the combustor downstream end and are configured for cooperating with the vane teeth for sealing each can combustor to turbine interface; wherein at least a seal is a honeycomb seal device, the honeycomb seal device being characterized in that the honeycomb seal device is an assembly comprising a honeycomb body made of a plurality or radial cells and a shield body covering at least the part of the honeycomb body cooperating with the vane tooth; wherein each groove and the honeycomb body have a annular extent; the honeycomb body comprises a front face directed towards the turbine, an opposite back face facing the bottom of the groove, an inner face facing the inner surface of the groove and an outer face facing the outer surface of the groove; the shield body covering the front face and part of the inner face and the outer face of the honeycomb body; wherein the honeycomb body discloses a T-cross section wherein an upstream portion has a radial extent higher than a downstream portion; the shield body covering either the entire inner face and the outer face corresponding to the downstream portion of the honeycomb body, or only a part of the inner face and the outer face corresponding to the downstream portion of the honeycomb body.