GAS-TURBINE ENGINE COMBUSTION CHAMBER BURNER

摘要

gas-turbine engines. SUBSTANCE: burner of gas-turbine engine combustion chamber includes fuel injector and tangential swirling device in form of passages with open ends and blades inside and near rods mounted in inter-blade passages. Each rod is mounted below trailing edge of respective blade. Number of rods is equal to number of blades. Diameter of circumscribed circle of rod exceeds thickness of blade cross-section. Cross-section of each rod is symmetrical to surface of trailing edge of respective blade whose surface is directed towards adjacent rod. Diameter of circumscribed circle of rod ranges from 0.245 to 0.5 of distance between trailing edges of adjacent blades or pitch of adjacent rods. Each rod is connected with trailing edge of respective blade. Each rod is mounted at distance from trailing edge of respective blade not exceeding half pitch of adjacent rods. EFFECT: reduced toxicity of combustion products; reduced carbon deposit and black deposit due to microturbulence in area of mixing jets of gaseous fuel with revolving flow of air. 3 cl, 3 dwg