COMBUSTION MODULE AT CONSTANT VOLUME FOR GAS TURBINE ENGINE Russian patent published in 2020 - IPC F02C5/12 F23R7/00 F01D17/14 

FIELD: machine building.

SUBSTANCE: combustion module (10) of a gas turbine engine, in particular an aircraft gas turbine engine, is configured to perform combustion at a constant volume and comprises at least one combustion chamber (12) located around axis (A). Chamber (12) comprises compressed gas inlet passage (16) and exhaust gas outlet passage (18), corresponding to rotating inlet (28)/outlet (30) valve, each associated with inlet (16) and outlet (18) passage and coaxial with said axis (A). Each inlet (16)/outlet (18) passage is made with possibility of opening or closing by rotating inlet (28)/outlet (30) valve. Module (10) comprises multiple combustion chambers (12) distributed in angular direction uniformly around said axis (A). Inlet passages (16) of combustion chambers (12) are made with possibility of opening or closing by common rotating inlet valve (28). Outlet passages (18) of combustion chambers (12) are made with possibility of opening or closing by common rotating exhaust valve (30) in compliance with the cycle containing the phase of fresh air inlet and exhaust gas blowing, the combustion phase and the discharge phase.

EFFECT: invention is aimed at improving tightness of rotating valves.

10 cl, 14 dwg