Geared turbomachine fan and compressor rotation

A gas turbine engine comprising:

• a propulsor section including a propulsor rotor and at least one propulsor blade;
• a compressor section including a compressor inlet having an entrance at a splitter, a first compressor and a second compressor, wherein the first compressor includes a plurality of stages, and the second compressor has a pressure ratio greater than 20, wherein the at least one propulsor blade is forward of the splitter relative to an engine longitudinal axis;
• a geared architecture having an input, an output, and a gear reduction ratio of greater than 2.3;
• and
• a turbine section including a first turbine and a second turbine, wherein the first turbine is connected to the second compressor, wherein the geared architecture interconnects the second turbine with the first compressor and the propulsor rotor, and wherein the second turbine includes an inlet, an outlet and a pressure ratio greater than 5, and the pressure ratio is pressure measured prior to the inlet as related to pressure at the outlet;
• wherein the first compressor includes a first compressor rotor that rotates together with the propulsor rotor at a common speed and in the same direction with the output of the geared architecture in operation.