| 摘要 |
<p>The invention relates to a turbine blade (1) for a gas turbine, comprising one after the other along a blade axis (11) towards a turbine blade tip (29), a platform region (13) and a airfoil (15) attached to said platform region, the airfoil (15) comprising an airfoil main body (12) and an airfoil tip shelf (17), the airfoil main body (12) comprises integrally formed a suction side wall (14) and a pressure side wall (16) bordering at least one cavity (37), wherein the cavity (37) is covered by said airfoil tip shelf (17), which is separately manufactured from the airfoil main body (12). In order to specify a turbine blade, in which improved cooling of the airfoil tip is provided and which is especially simple to produce for saving both time and costs, it is suggested that the suction side wall (14) and the pressure side wall (16) of the airfoil main body (12) both having a wall thickness (63) along its span direction, which in tip region (27) is constant.</p> |
