There is no steady torque applied to a jet engine by the airflow, due to the stators as noted by barit1 above.
There are still (I believe small) torque effects from the rotating parts, both gyroscopic - from changing the orientation of the engine - and inertial - from changing the engine's rotational speed. Both depend on the angular momentum of the shaft/blades, which scales with the angular speed, and the moment of inertia - an averaged/integrated product of mass and the square of the distance of the mass from the axis.
Most of the mass in a jet is in the shaft, relatively little in the blades, making for a small moment of inertia, whereas a propeller has more mass further off axis. The gyroscopic rotation in the horizontal plane when changing pitch, and the counterrotation effect along the shaft axis when changing the rpm should both be much less significant for a jet than a propeller of the same power.