| 摘要 |
<P>PROBLEM TO BE SOLVED: To improve heat transfer characteristics of a gas turbine component. <P>SOLUTION: An improved nozzle vane for a gas turbine engine includes: a vane wall having inner and outer wall surfaces while these wall surfaces are separated from each other so as to demarcate a plurality of fluid communicating passages for a cooling medium; individual cavities which are located in the fluid communicating passages for the cooling medium, and formed by an inner wall member arranged between the inner and outer wall surfaces; a plurality of impingement cooling sleeves arranged in the individual cavities to be defined by the inner and outer wall surfaces and the inner wall members; and a plurality of non-round, e.g., serrated, openings in each of the impingement cooling sleeves, with the openings being sufficient in size and number to accommodate the flow of a cooling media. <P>COPYRIGHT: (C)2013,JPO&INPIT |
