Is overall pressure ratio same as compressor pressure ratio for a gas turbine engine?
Modern turbofan engines typically have several stages of compression, the overall pressure ratio is the ratio of the highest pressure to the intake pressure. But the pressure ratios of each compressor can be a different.

The fan and booster add a bit of compression, followed by an optional intermediate pressure compressor and finally the high pressure compressor.

Because of these multiple shafts and therefor having some parts of the compressors not working on their design point you probably won't get accurate results by simulating a single stage compressor.