Air International 2021-10
A.Mladenov - After the burn
The original AL-41F, still a classified design, is an afterburning turbofan in the 44,080lb st (19.62kN) class, developed in the 1990s for the Mikoyan 1-44 fifth-generation fighter prototype seen here
The hydro-electronic engine control system used on the AL-31F and AL-31FP, as seen here, grants stable operation at speeds up to Mach 2 and at negative air speeds up to 110kt (200kph) as well as in controlled, inverted and flat spin
Su-30SM’s differential engine thrust is controlled by the aircraft’s fly-by-wire flight control system, without any additional pilot command inputs. This enables the heavyweight fighter to remain controllable at very low, or even zero, airspeed
The first AL-41F1-S order received at the UEC-UMPE called for engines for 48 aircraft, plus spares, to power the Su-35S' Gen 4++ fighters ordered for the Russian Air Force in 2009 and delivered in 2011-15
According to Sukhoi chief test pilot, Sergey Bogdan, the Su-35, powered by a pair of AL-41F-1S engines, is capable of supercruising, exceeding Mach 1.1 speed at military power setting at certain altitudes and low fuel-load states
The Su-35’s fully integrated flight and propulsion control operates the AL-41F-1S engines with movable nozzles that deflect through 15° up and down, and are canted at 32° outwards to longitudinal engine axis
The Chengdu J-10 is a mass-produced multi-role fighter for the PLAAF. It's powered by the Salyut-made AL-31FN afterburning turbofan, supplied to CHina in three subversions, known as Series 1, Series 2 and Series 3.
The Su-34 frontal bomber comes powered by the AL-31F-1M engines, also known as the AL-31F Series 42
The Su-57 features a deep integration of the engine control system and the aircraft’s flight control system, through use of the integrated flight and propulsion control concept, to provide performance gains
Su-57's AL-41F-1S engine generates 31,960-33,060lb st (14.22-14.72kN) of thrust and comes endowed with Gen 5 engine performance in terms of dry weight, thrust-to-weight ratio and specific thrust