User:Manderallen70/sandbox

This Turbojet was developed by a team led by Khachaturov on the basis of their preceding R-29 engine. The engine is the basis of the improved R-35 turbojet. Main improvements are attributed to an improved compressor that can handle higher temperatures.

R-35-300: Main Production version. This model is used in the Mig-23ML,MLA and MLD.

Type: Two-shaft turbojet with afterburner

LP Compressor: Five-Stage. Mass flow 110kg (242.5 lb)s.

HP Compressor: Six-Stage. Pressure ratio 13.0.

Combustion Chamber: Annular, with downstream vaporizing burners. Configured for minimal visible smoke.

HP Turbine: Single-Stage with cooled blades. TET 1,220 degrees C.

LP Turbine: Single-Stage.

Afterburner: Fully modulated, with soft light-up and single-lever control to maximum. Convergent/Divergent hydraulically controlled variable nozzle.

Dimensions:

Length:                                       4,975 mm (195.9 in)

Diameter:                                       912 mm (35.9 in)

Weight, Dry:                                 1,765 kg (3,891 lb)

Performance Rating: (S/L, ISA) Max T-O:                                  127.46 kN (28,660 lb st)

Max dry:                                   83.85 kN (18,850 lb st)

Specific Fuel Consumption: Max T-O:                              55.32 mg/Ns (1.96 lb/h/lb st)

Max dry:                              27.09 mg/Ns (0.96 lb/h/lb st)