| 摘要 |
<p><P>PROBLEM TO BE SOLVED: To cool a shroud and nozzle of a gas turbine. <P>SOLUTION: A segment of a component for use in the gas turbine includes a leading edge (4); a trailing edge (6); a pair of opposed lateral sides (20) between the leading and trailing edges; and a seal slot (18) provided in each lateral side. The seal slot includes a surface (22) having channels (30 and 36) extending in an axial direction defined from the leading edge to the trailing edge, at least one inlet (28 and 38) to the channel, and at least one outlet (32 and 40) from the channel. The at least one outlet is spaced downstream from the at least one inlet in the axial direction. The segment may be an inner shroud segment or a nozzle segment. <P>COPYRIGHT: (C)2011,JPO&INPIT</p> |
