From what I know, they tweaked to it to perform better at the cost of engine life down to 2200 from 4000.
Coz it is RD-93MA vs RD-93. The MA has real implicationsHow can thrust output go to 94KN for the same RD-93 rated at 86KN?
I have not seen an official mention of 94kN on the JF-17 officially. Please share if you have that
"The most significant difference being the repositioning of the gearbox along the bottom of the engine casing." The Klimov poster at Zhuhai 2010 airshow gave the thrust range of the engine to be 79 kN Dry to 98 kN Wet. This was designed specifically for FC-1 with increased thrust and relocated gearbox compared to base RD-33's. Although the increase of thrust decreased the service life of RD-93 to 2200 hours from RD-33's 4000 hours. According to Air Commodore Mehmood engines are solid and reliable: “We’ve flown 7,000 hours with the engine and we haven’t had any problems”, he said
It clearly states Maximum Engine Thrust is 19000lbs = 84.5KN. Same as it was on the previous blocks.