Essentially true, but you miss a lot of points
1> Density of liquids is typically in the range of ~600 times the density of liquids - so the fuel supply system to the nozzle have to be appropriately sized if you are trying to provide the same fuel heat content.
2> The Hydrogen to Carbon ratio of natural gas is higher than liquid fuels (substantially higher) - so the air requirement for the same heat released is changed. You now have to fix the air flow (since the air compressor is run by the same gas turbine you now need to adjust that)
Frame gas turbines which are designed for stationary use - have the real estate (space) for going to even low BTU gas. Aero-derivatives ( air plane engines converted for power production or drivers) have limited real estate available and fuel flexibility issues.
3> Depending on the air emissions permit - NOx needs to be looked into. If the turbine has Ammonia based SCR - you are probably okay. If not, you have to consider DLN (Dry low nox burners) - which essentially let the combustion processes happen in stages - limiting the amount of oxygen in each stage.
4> The Nozzle design will also need to look for how far the flame sits from the surface of the nozzle for lifing of the nozzle - steam injection or water injection is not uncommon.
This thread has a lot of good information and a lot of jumbled / misinformation. If I find some time, I will try to clear things up.