GAS TURBINE ENGINE COMBUSTION AFTERBURNER FRONT DEVICE Russian patent published in 2018 - IPC F02K3/10 

FIELD: motors and pumps.

SUBSTANCE: invention relates to the field of aviation gas turbine engines, namely to the aircraft gas turbine engines afterburn combustion chambers. Summary of invention is in the fact that the flame stabilizers are made in the form of hollow, streamlined bodies with closed lower part, the stabilizers inner cavity is divided into N longitudinal channels with possibility of the air supply therein and fuel, on the channels side walls the holes are made along the entire length. Flame stabilizers execution in the form of streamlined bodies ensures their uninterrupted flow in the GTE unboosted operation modes, which allows to reduce the full pressure losses. In the GTE afterburning operation modes, to create recirculation flow zones through openings on the channels side walls air jets are blown into the afterburner flow part, and fuel is injected into these zones, i.e. the flame stabilizers act as the fuel manifolds. Absence of separate fuel manifolds in the gas flow allows to further reduce the total pressure losses.

EFFECT: reduction of total pressure losses due to use of the bodies with streamlined form as flame stabilizers with the organization of the air jets injection from their surface in the GTE unboosted operation modes.

1 cl, 1 dwg