Gas turbine engine flame tube cooling system and integral swirler arrangement
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United States of America Patent
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-
Jun 16, 1998
Grant Date -
N/A
app pub date -
Dec 12, 1995
filing date -
Dec 16, 1994
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A system is provided for cooling especially the backplate of a flame tube of a combustion chamber for gas turbine engines, of the type having at least one burner arranged on the backplate and having a fuel nozzle and at least one swirler arranged coaxially with the fuel nozzle for the supply of combustion air. The backplate is cooled with compressed air diverted from a compressor and ducted to a head end of the combustion chamber. The backplate forms at least one cooling air duct to carry the compressed air supplied for backplate cooling, and the cooling air duct communicates at its outlet end at the burner with the flame tube such that the compressed air issuing from the cooling air duct enters into combustion in the primary zone. At its outlet end the cooling air duct can communicate with the air inlets of at least one swirler.
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