AIRCRAFT GAS TURBINE ENGINE COMBUSTION CHAMBER Russian patent published in 2017 - IPC F23R3/16 

FIELD: power industry.

SUBSTANCE: aircraft gas turbine engine combustion chamber, where the combination of the main combustion chamber and afterburner into a single chamber is realized. The combustion chamber has two combustion areas: the main and the afterburner. The main area is permanent, the afterburner is for chamber working at the augmented rating. The positive result is due to the fact, that the combustion conditions in the main combustion chamber afterburner area of at the same values of the total air excess ratio is objectively better, than in the afterburners of similar gas turbine engines.

EFFECT: invention allows to expand the operating modes range of the main combustion chambers according to the total air excess ratio.

6 cl, 3 dwg