| 摘要 |
PROBLEM TO BE SOLVED: To provide a gas turbine component in which combustion is performed. SOLUTION: The gas turbine component includes a liner (10) including a first surface (11) facing a first space (13) and a second surface (12) facing a second space (14), the liner being interposed between the first and second spaces (13, 14) and having a through-hole (20) defined therein extending from the first surface (11) to the second surface (12) by which incoming flows proceed from the first space (13) and to the second space (14). At least the first surface (11) is formed, so as to resist against separation from the sidewalls of the through-hole (20) through the adjustment of the incoming flows. COPYRIGHT: (C)2010,JPO&INPIT |
