| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a blade used for a gas turbine, which is significantly improved in cooling. <P>SOLUTION: A blade 10 is used for a gas turbine, the blade 10 has an airfoil 11, and a blade wall 18 of the airfoil 11 encloses an inner chamber 17. For cooling the blade wall 18, a cooling arrangement 19 is disposed in the blade wall 18, the cooling arrangement 19 has a radial passage 20 extending in the longitudinal direction of the blade. From the radial passage 20, a multiplicity of cooling passages 21, 22, extending in the blade wall 18, branch in the transverse direction, and from the radial passage 20, a multiplicity of film-cooling holes 23 are extended to the outside in the transverse direction. The distribution of film-cooling holes 23 along the radial passage 20 is selected independently of the distribution of the cooling passages 21, 22 along the radial passage 20. <P>COPYRIGHT: (C)2013,JPO&INPIT |
