Reverse flow combustion chamber, especially reverse flow ring combustion chamber, for gas turbine propulsion units, with at least one flame tube wall film-cooling arrangement
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United States of America Patent
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Feb 9, 1988
Grant Date -
N/A
app pub date -
Nov 19, 1986
filing date -
Nov 19, 1985
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
A reverse flow combustion chamber includes an annular chamber enclosed between flame tube wall sections to which cooling air is so supplied from an outer annular channel acted upon with secondary air opposite the main flow direction in the flame tube in such a manner that the cooling air that it is blown out in the opposite flow direction film-like against an adjoining flame tube wall. For the purpose of a cooling film with extremely great travel length which is homogeneous over the entire circumference, the annular chamber is to be constructed flat elliptically in the combustion chamber longitudinal direction in such a manner that together with air catching or collecting bores which terminate radially and essentially tangentially in the downstream end of the annular chamber--in relation to the secondary flow--, a part of the supplied cooling air produces an independent recirculation vortex following the elliptical annular chamber contour which is provided for the equalization of the main cooling air flow supplied by way of the air collecting bores and deflected into the flame tube through about 90.degree. in the direction of the main flow.
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