A conventional helicopter has three main flight controls.
Torque pedals : these function is a similar way to the rudder on a fixed wing aircraft. They work by adjusting the pitch of the blades of the tail rotor to produce more or less thrust, allowing the pilot to balance the torque from the rotor blades and also control the yaw of the aircraft.
The cyclic lever : this controls the pitch of individual rotor blades at a specific point in their rotation, controlling pitch and yaw. This is analogous to tilting the rotor disk at about its centre.
Collective pitch : this controls the pitch of all of the rotor blades simultaneously controlling overall lift. As the pitch is changed the throttle must also be used to adjust engine power to maintain a more or less constant rotational speed as the load on the blades changes.
It is worth reiterating that it is the pitch of the blades which provides the direct control over thrust and lift and engine power is adjusted to keep their rotational speed withing an optimum range.
In a conventional helicopter the tail rotor and main rotor are directly coupled together via the gearbox and only their blade pitch rather than speed can be adjusted independently ie the tail rotor speed is proportional to the main rotor speed.
There are designs which deviate from the conventional layout though for example there are tail designs which use ducted airflow rather then an external rotor and also various configurations of twin rotor which dispense with tail thrust altogether eg the Chinook which has fore and aft rotors and various
Russian military helicopters which have coaxial rotors.