Aircraft engine combustion liner cooling apparatus
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United States of America Patent
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-
Sep 12, 1989
Grant Date -
N/A
app pub date -
Apr 29, 1988
filing date -
Apr 29, 1988
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
Aircraft engine cooling apparatus having a plurality of cooling gas inlet nozzles, producing first streams of cooling gas moving in a forward direction, a plurality of first direction reversal members for splitting the first streams into second and third streams straddling the nozzles, and substantially reversed in direction relative to the direction of the first streams, a plurality of second direction reversal members, positioned between pairs of adjacent nozzles, for again substantially reversing the directions of the second and third streams, while combining the second and third streams to form a fourth stream of laminar flow cooling film, and wherein adjacent pairs of the first direction reversal members have wall portions configured to form gradually diverging channels through which the fourth stream cooling film moves.
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