Why is tangential velocity a loss of kinetic energy in a turbine section? While researching turbine engines I came across a statement

The mass of airflow naturally does not change in the transfer of energy to the rotor system, but the velocity of mass flow being slowed axially is said to account for the energy of flow as the energy of shaft power is increased. In other words, tangential velocity is essentially a loss of kinetic energy to the engine.

Why and how does this the loss occur, and how can this loss be reduced?
I'm not trying to get an in-depth mathematical aspect on that topic as I'm still a beginner with the study of gas turbines, a simpler theoretical non-math explanation would very much be appreciated, thanks!
We take axial flow turbines as our example here.
Tangental flow of air (flow that circulates around the engine's central axis) is imparted to the air by viscous drag between the air and the rotating fan and compressor blades. Between those fan discs are stator blades that act to straighten out the tangental flow and help convert the kinetic energy of the axial flow into pressure rise in the compressor stage. Viscous drag losses occur in the stator stages too as they perform this function. These losses dissipate some of the compression work being performed on the air by the compressor as a whole, and that amount of work then cannot contribute to thrust generation in the engine.