AVIATION GAS-TURBINE ENGINE Russian patent published in 2008 - IPC F02K1/82 F02K1/12 

FIELD: motors and pumps.

SUBSTANCE: aviation gas-turbine engine includes afterburner at turbine outlet continued with nozzle and limited by heat-reflecting casing in radial direction. Heat-reflecting casing is installed inside crankcase. Crankcase together with heat-reflecting casing form circular channel, where cold secondary flow circulates during engine operation. Circular diaphragm is installed at the circular flow outlet and connected rigidly with the above crankcase. The nozzle contains a multiple set of chokes. Their ends are pin-connected with crankcase. Each choke is provided with heat-reflecting plate on its internal side. Together with choke, heat-reflecting plate hinders the passageway where cooling air is supplied through diaphragm. Cooling air supply to passageways is provided by circular channel limited by the first flexible circular gasket from the outside. During engine operation, circular gasket is held in the position of sliding stopper in the direction to outlet internal side of crankcase and inlet internal side of chokes under the pressure of cold secondary flow. On the inside, channel is limited by the second flexible circular gasket. Inlet end of gasket is fixed on radial internal diaphragm zone. Outlet end of gasket is in the position of sliding stopper in the direction of inlet internal side of heat-reflecting plates.

EFFECT: improvement of operating engine characteristics of engine by avoiding secondary air leaks between circular channels and chokes.

10 cl, 10 dwg