| 摘要 |
aircraft engineering. SUBSTANCE: liquid-propellant rocket engine, mainly with afterburning of generator gas, has combustion chamber with gas passages, straightening lattice and nozzle head, at least one turbopump set with axial-flow and gas turbine and coaxial gas generator located aside from combustion chamber, and at least one generator gas duct. The latter includes L-shaped elbow rounded off at corners with gas generator and gas turbine. Elbow is mated with combustion chamber through curved-axis diffuser gas passage with angle of curvature from 80 to 90 deg, with axes being located in one plane. Plane of rotation of gas turbine wheel is set at right angle to plane of butt- joining of exhaust branch pipe of turbine housing and intake branch pipe of combustion chamber gas passage. Plane passes through upper half of gas passage branch pipe bore in plane of butt-joining. EFFECT: increased specific thrust and high burning stability margins at simplified design and reduced mass of engine. 12 cl, 12 dwg |
