The fuel is partially burned in a pre-chamber to produce high pressure, hot gases that drive the turbo-pumps (fuel pumps). The fuel is then fully burned in the main combustion chamber and the exhaust gases (water vapor) leave the nozzle at approximately 6,000 mph (10,000 km/h). Each engine can generate between 375,000 and 470,000 lb (1,668,083 to 2,090,664 N) of thrust; the rate of thrust can be controlled from 65 percent to 109 percent maximum thrust. The engines are mounted on gimbals (round bearings) that control the direction of the exhaust, which controls the forward direction of the rocket
100% is probably something like Max sustainable burn. 109% is probably something that could be temporarily be boosted to. IE T-0 to T-15 then sustain the 65% as it exits the atmosphere and less thrust is required.
It could also mean that 100% is full burn… then with an afterburner section it could give that extra 9% thrust.