DEVICE AND METHOD (VERSIONS) TO STABILISE FLAME IN TURBOJET ENGINE AFTERBURNER CHAMBER Russian patent published in 2010 - IPC F02K3/10 F23R3/18 

FIELD: engines and pumps.

SUBSTANCE: proposed device comprises jet aerodynamic flame stabiliser with fuel nozzle and combustion chamber with fuel-air mix igniter, extra small-size gas turbine engine, as well as air intake branch pipes, exhaust gas discharge device and system of supersonic nozzles. Small-size gas turbine engine compressor is arranged ahead of fuel nozzle and combustion chamber, and its turbine is arranged behind combustion chamber. Proposed method used air jets forced into afterburner chamber gas flow via system of supersonic nozzles, towards it and at an angle to it. Air is bled from engine compressor intermediate stage. Jet pressure required to stabilise flame is produced using said extra small-size gas turbine engine arranged inside afterburner chamber. In compliance with the first version, proposed method differs from known designs in that air is bled from compressor intermediate stage. Note here that jet pressure required to stabilise flame is produced using said extra small-size gas turbine engine arranged inside afterburner chamber. In the case of two-stage turbojet engine, air is bled from the second stage.

EFFECT: reduced pressure loss in afterburner chamber, stable firing at afterburner modes.

3 cl, 2 dwg