FIELD: aeronautical engineering.
SUBSTANCE: invention relates to aeronautical engineering, namely to a method for manufacturing a flame tube (FT) of a combustion chamber, and can be used in the manufacture of cooled flame tubes of combustion chambers with tunnel cooling, mainly for small-sized gas turbine engines. According to the invention, the shaping of the shells of the outer shell 9, the outer wall 5 and the inner screen 10 of the flame tube is carried out by the method for rotational drawing, and the cooling channels are formed in the form of windows 21 evenly spaced around the circumference of the shell of the outer wall with guide elements, separated by corresponding bridges. To form the windows, corresponding through open slots are made, and to form the guide elements, sections of the shells 16 of the outer wall 5 of the flame tube are bent, located between the corresponding through slots, and in the direction opposite to the direction of the cooling flow. In the process of assembly, the inner screen 10 of the flame tube is installed with the possibility of axial movement relative to the shells of the outer shell 9 and the outer wall 5 of the flame tube, and the latter are fixed relative to each other by gap-free mating of the end part of the outer shell with the end part of the outer wall facing it.
EFFECT: invention makes it possible to reduce the complexity of manufacturing while ensuring reliability by eliminating the deformation of the flame tube during its operation at elevated temperatures.
2 cl, 6 dwg
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Authors
Dates
2022-11-08—Published
2022-04-08—Filed