FIELD: engines and pumps.
SUBSTANCE: gas turbine circular combustion chamber comprises outer and inner axial walls and chamber bottom jointing together the said axial walls. Aforesaid bottom incorporates multiple jet and perforated orifices. The said jet orifices are intended for, at least, injecting fuel inside the combustion chamber. The said perforated orifices serve to let airflow in to cool down the chamber bottom. The said bottom comprises, on the one side, an outer section with perforated orifices letting a portion of airflow to pass along the outer axial wall, and, on the other side, an inner section with perforated orifices letting another portion of airflow to pass along the inner axial wall. In any axial half-section passing between two jet orifices, following each other, the values of acute angles formed between, at least, half-section central line located between the outer and inner axial walls, and the main directions of perforated orifices of the outer section of the given half-section, decreases depending upon the distance of perforated from this, in fact, central line. The values of acute angles formed by, in fact, central line and main directions of perforated orifices of the inner section in the given half-section decreases depending upon the distance of perforated from this, in fact, central line.
EFFECT: higher efficiency of cooling combustion chamber walls.
4 cl, 4 dwg
