RU-19A-300

Auxiliary turbojet engine, with a seven-stage axial-flow compressor with air bypass due to the fourth stage, an annular combustion chamber, a single-stage axial-flow jet turbine and a jet nozzle with an unregulated outlet section. The engine consists of an axial-flow 7-stage compressor with air bypass behind the fourth stage, an annular combustion chamber, a single-stage shrouded turbine and an unregulated jet nozzle. The nozzle is tilted downward by 10 °.

RU-19-300 - basic.

RU-19A-300 - modified. Installed on the An-26.

Developed at OKB-300.

The RU 19A-300 turbojet engine is designed for installation on an aircraft as an additional power plant for the An-26.

Provides the following tasks:

1. Creation of additional thrust during takeoff in order to increase the payload and ensure flight safety in the event of a main engine failure, as well as during climb in hot climates;
2. Onboard starting of the main engines; Increase in thrust-to-weight ratio in flight in case of main engine failure;
3. Supply of the aircraft on-board network with electricity in case of failure of the main engine generators;
4. Supplying the aircraft on-board network with electricity when the main engines are inoperative in the parking lot.

The engine runs on T-1, TS-1, T-2 aviation kerosene.