EJECTOR-TYPE THRUST BOOSTER OF GAS-TURBINE ENGINE Russian patent published in 2000 - IPC

FIELD: gas-turbine jet engines. SUBSTANCE: thrust booster has variable-section annular mixing chamber accommodating multiple-nozzle engine device forming, together with chamber, inlet section and mixing section. Inner wall of chamber in mixing section is contracting from nozzle assembly towards outlet sectional area F_out= (6,5-40)ΣFo, where F_out is outlet sectional area of mixing chamber; ΣFo is total outlet sectional area of nozzles; outlet sectional area of mixing chamber is in the middle of nozzle edges: L = (0,35-1,4)D_out, where L is mean distance between nozzle edges and outlet sectional area of mixing chamber; D_out is diameter of outlet sectional area of mixing chamber; angle of inclination of inner wall in mixing section to its axis is 5-17 deg. EFFECT: improved thrust at same fuel consumption.