FIELD: gas turbine engines.
SUBSTANCE: invention relates to the combustion chambers of gas turbine engines. The fuel injector contains a plurality of channels and includes: a first channel through which fuel or combustion air passes, a second channel through which fuel or combustion air passes and which is different from the first channel, and the fuel injector includes structural elements, and an integral structural element of the fuel injector of these structural elements is at least the area in which the first channel and the second channel are located. The first channel and the second channel are divided into a plurality of sections arranged in the circumferential direction of the fuel injector.
EFFECT: invention makes it possible to obtain a fuel injector with low thermal stress caused by the temperature difference between the fuel and combustion air that pass through it, as well as to increase the reliability and service life of the gas turbine combustion chamber.
10 cl, 8 dwg
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