| 摘要 |
The invention relates to a turbine blade ( 63, 65 ) comprising a vane ( 67, 69 ) that runs along a blade axis ( 73, 75 ) and a platform region ( 61 ), which is located at the root of the vane ( 67, 69 ) and has a platform ( 71 ) that extends transversally to the blade axis ( 73, 75 ). The aim of the invention is to configure a delimitation ( 87 ) of a flow channel ( 5 ) of a gas turbine ( 1 ) in the simplest possible manner. To achieve this, the platform ( 71 ) is configured by an elastic sheet metal part ( 77, 79 ) that rests on the vane ( 67, 69 ). Said part leads to a gas turbine ( 1 ) comprising a flow conduit ( 5 ) that runs along an axis ( 3 ) of the gas turbine ( 1 ), said conduit having an annular cross-section for a working medium (M) and a second ( 9, 13 ) vane stage ( 7, 9, 11, 13 ) that is situated downstream of a first ( 7, 11 ) vane stage, which runs along the axis ( 3 ). According to the invention, a vane stage comprises a number of turbine blades ( 63, 65 ) that are arranged in a ring and extend radially into the flow channel ( 5 ) in accordance with the inventive concept.
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