FIELD: machine building.
SUBSTANCE: gas turbine engine combustion chamber includes at least one wall limiting the combustion chamber and having a hole for passage of the incoming part. Said incoming part comprises at least one hole in its part located inside combustion chamber, made with the possibility of creation of air cooling film of the zone at the outlet of the fitting part. Inner surface of said at least one wall comprises two plates arranged parallel to each other and configured to create an air cooling film of said at least one wall, wherein the incoming part is between two plates.
EFFECT: invention is aimed at increasing the service life of the combustion chamber with maximum reduction of temperature gradients and local hot spots.
11 cl, 7 dwg
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