FIELD: power engineering.
SUBSTANCE: gas turbine engine (GTE) combustion chamber comprises a body, a flame tube, which has outer and inner walls, and a board of circular shape with nozzle modules installed on it and the main fuel header connected with the board, the cavity of which is connected by fuel channels with nozzle modules, inner and outer bodies, inner and outer jackets installed with a gap relative to the inner and outer bodies. The number of nozzle modules is made as multiple to four. Nozzle modules are installed in two rows: inner and outer. Additionally there are two fuel headers: inner and outer, The cavity of the outer header is connected by fuel channels with each nozzle module via one in the outer row of nozzle modules. The cavity of the inner header is connected with each nozzle module via one in the inner row. The main fuel header is connected with remaining nozzle modules of both rows. Between the board and the outer and inner walls of the flame tube there are accordingly installed outer and inner facilities for supply and swirling of cooling air with the possibility to supply air at sharp angle to the axis of the flame tube, comprising blades installed at the angle to the axis of the combustion chamber. On the walls of the flame tube along the circumference there are "pockets" installed, which are made in the form of hollow streamlined profiles directed towards the axis of the flame tube. Holes are made in the outer and inner jackets in the rear part along the flow.
EFFECT: increased completeness of fuel combustion and reduced emission of hazardous substances at all modes, and provision of even temperature field at the outlet of combustion chamber along circumference at all modes, the axis of the nozzle module.
8 cl, 13 dwg
