Gas turbine engine afterburner
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United States of America Patent
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Apr 28, 2020
Grant Date -
Nov 30, 2017
app pub date -
Jul 28, 2017
filing date -
Mar 8, 2013
priority date (Note) -
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Abstract
An afterburner for use with a gas turbine engine includes a plurality of vanes distributed downstream of a turbine of the gas turbine engine. The vanes can include one or more exit apertures through which hot combustion flow from a pilot can be injected. The exit apertures can be protrusions or slots in some forms. In some embodiments, cooling passages are arranged around the exit apertures. An upstream vane portion can be positioned to inject fuel to be combusted via interaction with hot flow that is discharged through the exit apertures.
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