Boundary layer cooling air for embedded engine
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United States of America Patent
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Mar 2, 2021
Grant Date -
Jan 25, 2018
app pub date -
Jul 22, 2016
filing date -
Jul 22, 2016
priority date (Note) -
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Abstract
A gas turbine engine has an inner housing surrounding a compressor, a combustor, and a turbine, with an inlet leading into the compressor, and a cooling sleeve defined radially outwardly of the inlet to the compressor for receiving cooling air radially outward of the compressor inlet. The cooling sleeve extends along a length of the engine, and radially outwardly of the inner housing, with the cooling air in the cooling sleeve being ejected at a downstream end to mix with products of combustion downstream of the turbine. An aircraft is also disclosed.
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