GAS-TURBINE ENGINE Russian patent published in 2005 - IPC

FIELD: mechanical engineering.

SUBSTANCE: proposed gas-turbine engine contains rotor, compressor, combustion chamber and turbine. Combustion chamber consists of separate chambers uniformly spaced over circumference and installed on outer circumferential surface of combustion chamber. Each chamber is made in form of solid of revolution and is provided with one port aligned with corresponding port in combustion chamber housing. Auxiliary rotor mounted inside combustion chamber housing has at least one air supply channel and at least one outlet channel to direct hot gas from combustion chamber into turbine. Inlet port of air channel is located on radial surface of auxiliary rotor tightly adjoining compressor housing. Outlet port of air channel is located on outer circumferential surface of auxiliary rotor tightly adjoining inner circumferential surface of combustion chamber housing. Outlet part of air channel adjoining outlet port of air channel has mainly circumferential direction for tangential delivery of air into chambers. Inlet port of outlet channel is located on outer circumferential surface of auxiliary rotor. Outlet port of outlet channel is located on radial surface of auxiliary rotor tightly adjoining turbine housing. Outlet port of air channel and inlet port of outlet channel located on outer circumferential surface of auxiliary rotor have sections for simultaneous alignment with ports for scavenging the chambers and filling them with air. Auxiliary rotor has at least one bypass channel with inlet and outlet ports on outer circumferential surface designed for interconnecting chambers in which combustion process is completed and chambers filled with air, when auxiliary rotor rotates. Outlet section of bypass channel is made adjoining outer wall of auxiliary rotor mainly in circumferential direction for tangential delivery and rotation of bypassed gas flow in chambers in direction of rotation of air flow.

EFFECT: increased efficiency, provision of complete combustion of fuel in gas-turbine engine.

3 dwg