(EN) The invention relates to a cast turbine blade (10) having a platform (16) and a hollow blade airfoil (18) arranged thereon, wherein the blade airfoil (18) has a pressure-side blade wall (34) and a suction-side blade wall (32) that extend, along a centrally arranged curved profile centerline (42), from a common leading edge (28) to a common trailing edge (30), and having a transition (36), with anouter contour profile, between the blade airfoil and the platform (36), wherein the blade walls (32, 34) each have a locally determined blade wall thickness (D), wherein the turbine blade has, internally, a contour profile that partially matches the outer contour profile of the transition (36) such that the region of the transition (36) has an essentially constant blade wall thickness. In order tofurther improve the service life of such a turbine blade, it is provided that, in the transition (36), the contour profile at a surface section (40) of the blade airfoil facing the leading edge (28)is such that the blade wall thickness is increased there in comparison to the blade wall thickness of the transition away from the leading edge.
(ZH) 本发明涉及一种具有平台(16)并具有布置在其上的中空叶片翼型(18)的铸造涡轮机叶片(10)，其中叶片翼型(18)具有沿居中布置的弯曲外形中心线(42)从公共的前缘(28)延伸到公共的后缘(30)的压力侧叶片壁(34)和吸力侧叶片壁(32)，并且涡轮机叶片(10)具有在叶片翼型和平台(36)之间的具有外轮廓外形的过渡部(36)，其中叶片壁(32、34)均具有局部地确定的叶片壁厚(D)，其中涡轮机叶片在内部具有部分地适应于过渡部(36)的外轮廓外形的轮廓外形，使得过渡部(36)的区域具有基本均匀的叶片壁厚。为了进一步改善这种涡轮机叶片的使用寿命，提供了在过渡部(36)中，叶片翼型的面向前缘(28)的表面部分(40)处的轮廓外形使得：与远离前缘的过渡部的叶片壁厚相比，此处的叶片壁厚增加。