As the other answer says, flying to orbit on compressed CO2 is right out. Forget that approach.
However, if you are willing to use the CO2 as propellant in a nuclear thermal reactor, that has at least been looked at and found plausible for Mars applications, so maybe it could work at Venus.
Carbon Dioxide is the most readily accessible of all the candidate
martian propellants. Composing 95% of the atmosphere, it can be
obtained by pumping the martian air into a tank. At a typical martian
temperature of 233 K, carbon dioxide liquifies under a pressure of 10
bars. Under these conditions, assuming an isothermal compression
process, liquid CO2 can be manufactured for an energy cost of just
84 kW-hrs per metric ton. The NIMF engine produces over a thousand MW
(thermal). If an electrical capacity of 1 MWe is built in as well,
then the (2800 K, 40 MT) NIMF would be able to fuel itself for a
flight into a high orbit in less than 14 hours! Liquid CO2 has a
density 1.16 times that of water and is eminently storable under
(NIMF stands for Nuclear rocket using Indigenous Martian Fuel, dreadful acronym)
NIMF appears to have been conceived as a NERVA-like engine in which a nuclear reactor produces thrust by heating a propellant. Significant changes had to be made to use CO2 as the propellant.
The paper is here.