SMALL-SIZE COMBUSTION CHAMBER OF GAS TURBINE ENGINE Russian patent published in 2010 - IPC F23R3/16 

FIELD: engines and pumps.

SUBSTANCE: small-size combustion chamber of gas turbine engine includes housing, fuel-spray nozzle, start-up ignition plug and air supply channel located perpendicular to axis of chamber housing and changed to air-and-fuel channel. Air-and-fuel mixture channel is spiral and creates the mixture flow swirl angle increasing from 0° to optimum which is equal to 60°. Combustion chamber outlet is made in the form of diverging nozzle at the following ratios of parametres of channels and combustion chamber: d_in/d_sp=1.3-1.4; d_c/d_n=3.0-3.5; l_c/d_c=1.9-2.2, where d_in - diametre of radial channel inlet, d_sp - diametre of spiral channel inlet, which is equal to diametre of radial channel outlet, d_c - combustion chamber diametre, d_n -diametre of the nozzle inlet, l_c - combustion chamber length.

EFFECT: intensification of heat- and mass-exchange, protection of chamber walls against high temperature, decrease of mass and dimensions parametres, economy of heat-resistant materials and considerable reduction of content of nitrogen oxides in the turbine working medium.

4 dwg