Gas turbine engine
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United States of America Patent
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-
Oct 23, 2001
Grant Date -
N/A
app pub date -
Sep 25, 1998
filing date -
Sep 25, 1998
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A gas turbine engine has a turbine blade flow portion located between a blade inlet edge and outlet edge, and having a compressor to supply a fluid flow comprising a substantial portion of the compressor fluid output along the outside surface of the blade flow portion, thus providing a thermal insulating boundary layer for the turbine blades over which flows heated fluid from the combustor. Heated fluid formed in the combustor flows without further cooling directly to the turbine blades, thereby reducing losses associated with cooling.
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