FOLDING AFTERBURNER CHAMBER OF SMALL-SIZE GAS TURBINE ENGINE Russian patent published in 2024 - IPC F23R3/00 

FIELD: aviation; engine building.

SUBSTANCE: invention relates to aircraft engine building, particularly to small-size gas turbine engines for unmanned aerial vehicles, namely to design of elements of afterburner chambers. Small-size gas turbine engine folding afterburner comprises a system of external housings and a system of heat shields, including an acoustic liner, to form a cooling channel between the systems, a diffuser housing, a nozzle and a front device consisting of annular stabilizers and radial stabilizers. System of outer housings includes front housing, middle housing and rear housing, having conical centring surfaces between them. System of heat shields additionally comprises a rear shield, including ribs with openings between them and a flange with holes, wherein acoustic liner and rear shield have cylindrical centring surfaces. Also, the folding afterburner chamber of the small-size gas turbine engine additionally contains a fairing connected to the diffuser housing and the middle housing. At that, the rear housing together with the nozzle and the rear shield have the possibility of axial movement relative to the housing of the middle and acoustic liner, and the diffuser housing together with the middle housing, the fairing and the acoustic liner have the possibility of axial movement relative to the front housing. Annular gap between housing middle and acoustic liner is provided by ribs on rear shield, and annular gap between housing rear and rear shield is provided by ribs on rear shield and flange of rear shield.

EFFECT: increasing functional capabilities and reducing weight and size characteristics to ensure the engine placement in a limited space before its use due to the afterburner chamber folding while maintaining the structural elements reliability, with preservation of service life and without increase of thermal load on heat protective shield.

1 cl, 7 dwg