the invention relates to a turbine blade comprising a vane that runs along a blade axis and a platform region , which is located at the root of the vane and has a platform that extends transversally to the blade axis . the aim of the invention is to configure a delimitation of a flow channel of a gas turbine in the simplest possible manner . to achieve this , the platform is configured by an elastic sheet metal part that rests on the vane . said part leads to a gas turbine comprising a flow conduit that runs along an axis of the gas turbine , said conduit having an annular cross - section for a working medium and a second vane stage that is situated downstream of a first vane stage , which runs along the axis . according to the invention , a vane stage comprises a number of turbine blades that are arranged in a ring and extend radially into the flow channel in accordance with the inventive concept .