FIELD: engines.
SUBSTANCE: gas turbine engine with lengthwise axis defining the axial direction of engine comprises compressor, combustion section with multiple devices, turbine section, casing and shell air circulation system. Casing has part located around section of combustion containing casing wall, which has an upper part of the wall forming the top dead center, left and right side wall parts and lower part of the wall forming the lower dead point. Note here that this part of the casing additionally limits the internal volume containing devices for combustion and air, compressed by compressor section. Shell air circulation system contains at least one discharge element, located in lower part of the wall, which is a wall of the casing, the first and the second inlet elements located in upper part of the wall, which is a wall of the casing, inlet elements are located at certain distance from each other and are located in the same place in axial direction, system of pipelines providing connection by fluid between at least one outlet element and inlet elements, an air blower and valve system.
EFFECT: invention ensures uniform distribution of air temperature in combustion chamber.
20 cl, 3 dwg
