FLAME TUBE OF GAS TURBINE ENGINE COMBUSTION CHAMBER Russian patent published in 2017 - IPC F23R3/42 

FIELD: engine devices and pumps.

SUBSTANCE: combustion chamber flame tube of a gas turbine engine comprises a front device. On the device front plate there are burner modules with longitudinal axis collinear to flame tube axis with blade radial swirlers and mixing channels. The total area ratio of outlet holes of burner modules to total area of the front plate is in from 18 to 30. The blades of radial swirler are located at inlet to burner module mixing channel and installed at angle within the range from 48 to 53°. In the burner module mixing channel there is a central bushing with channel swirler having ducts for feeding air and fuel in a partition, made at an angle in the range 90…30° to the blade surface. The length of the mixing channel inner wall is 80…90% of its outer wall length. The ratio of outer diameter of the mixing channel inner wall to inner diameter of its outer wall is within 0.55…0.65. The distance from outlet plane of the mixing channel inner wall to channel swirler lies within 0.35…0.55 of the mixing channel wall inner diameter. There are no channels in one of the burner modules for running and feeding fuel into the central bushing. The channel swirler contains channels only for air supply.

EFFECT: reliable and stable operation of combustion chamber at low engine operation modes by means of non-pulsating combustion of fuel-air mixture in combustion chamber flame tube.

2 cl, 8 dwg