AIRCRAFT GAS-TURBINE ENGINE COMBUSTION CHAMBER BURNER UNIT Russian patent published in 2003 - IPC

FIELD: mechanical engineering; gas-turbine engines. SUBSTANCE: proposed combustion chamber burner contains scroll housing with nozzle and radial swirler with inlet channels installed at scroll housing inlet. Projections in form of dihedral angles with larger and smaller faces are made on inner surface of scroll housing. Larger face is inclined to side of inlet into swirler channels, and smaller face, in radius to swirler axis. Ratio of length of smaller face to length of larger face is 0.2-0.25, and face-to-face angle is 55^o - 80^o. EFFECT: increased range of stable operation of burner unit. 2 cl, 3 dwg