Use of multi-faceted impingement openings for increasing heat transfer characteristics on gas turbine components
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United States of America Patent
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Oct 6, 2015
Grant Date -
Jun 20, 2013
app pub date -
Dec 15, 2011
filing date -
Dec 15, 2011
priority date (Note) -
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Abstract
An improved nozzle vane for a gas turbine engine, comprising a vane wall having inner and outer wall surfaces, the wall surfaces being spaced from one another to define a plurality of fluid passageways for a cooling medium; discreet cavities formed by interior wall members disposed between the inner and outer wall surfaces and within the fluid passageway for the cooling medium; a plurality of impingement cooling sleeves disposed in the discreet cavities defined by the inner and outer wall surfaces and by interior 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.
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