Thermoelastic connection of the injector tube and the flame tube of a gas turbine
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United States of America Patent
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May 30, 1995
Grant Date -
N/A
app pub date -
Jul 16, 1993
filing date -
Jul 18, 1992
priority date (Note) -
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Abstract
The present invention pertains to a thermoelastic connection of a hot gas-carrying injector tube (8) to the flame tube (1) suspended in the combustion chamber housing (10) of a gas turbine. The injector tube (8) is connected by corrugated spacers (7) to a circumferential intermediate ring (6), which is attached to the lower flange of the flame tube (1) by detachable fastening elements (3, 4, 5). A circumferential cooling channel (annular space 15), into which cooling air is admitted, is formed between the cone of the injector tube (8) and the intermediate ring (6). The compressor air enters the combustion space (1, 8) of the combustion chamber (10) through the annular space (15) from below, as well as through the holes (11), especially through the circumferential gap (12).
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