A turbine, by definition, provides zero thrust, because it works the other way (it extracts energy from the flow).

What you meant to say was that the air flowing through the engine core provides very little thrust, because most of its energy is being extracted by the turbine almost immediately after combustion.

Thank you for correcting me. That is indeed what I meant.

Technically, the nozzle provides thrust in the hot gas path. Point taken though. In jet engines, you're correct, most of the power is robbed by the turbine. :-)

...which uses it to drive the compressor, which, together with the diffuser, is a significant source of thrust.

https://i.stack.imgur.com/47W9J.jpg

Note that here, the largest source of thrust is from the components that jets and rockets have in common (combustion chamber and the divergent section after the turbine) - though here, in a non-afterburning jet engine, the nozzle must be convergent rather than divergent, and that imposes a cost.