In regards to rocket launches, what rocket launch contained the most potential energy (joules/btu/etc.) in its thrust propellant to achieve is basic mission? I'm not as much concerned with differences between different specific launches of a given configuration, but in general? This should be for a rocket configuration that has actually been launched, whether it successfully reached orbit (i.e. Saturn V), or blew up on the way (i.e. N1). Nothing that is still only on the drawing board or only still in development (aka NASA SLS). If it tried actually to launch, it can be considered.
For convenience this doesn't need to include fuel used for purely maneuvering actions once in space (i.e. maneuvering thrusters) or onboard power (fuel cells, RTGs, etc.), but rather main propellants (whether solid or liquid) designed to alter the velocity of the spacecraft for mission purposes.
My guesses would be that the most potential launch energy would be between the Soviet N1, Soviet Buran, Saturn V, and US Space Shuttle, but not sure if there are other heavy lift vehicles that would be comparable.
I'm not quite sure how to properly word this question with the proper terminology, so please feel free to edit as appropriate.
I guess another way to basically ask this question, would be to ask which rocket would have (or did) make the biggest "bang" if it performed an unexpected very rapid highly exothermic deconstruction event at launch time? You can put Marvin the Martian's "There's supposed to be an Earth shattering kaboom!" quote here if you'd like.