Gas turbine engine compressor arrangement

A gas turbine engine comprising:

• a propulsor section including a propulsor having at least one blade;
• a core engine including a compressor section and a turbine section;
• a gear arrangement that drives the propulsor, the gear arrangement including an epicyclic gear train having a sun gear, a ring gear, and a plurality of intermediate gears arranged circumferentially about the sun gear and intermeshing with the sun gear and the ring gear, and the gear arrangement defining a gear reduction ratio of greater than 2.3:1;
• wherein the compressor section includes a first compressor and a second compressor downstream of the first compressor;
• wherein the turbine section includes a first turbine and a second turbine that drives an input of the gear arrangement, wherein the second turbine includes an inlet, an outlet, and a turbine pressure ratio greater than 5:1, wherein the turbine pressure ratio is a ratio of a pressure measured prior to the inlet as related to a pressure at the outlet prior to any exhaust nozzle, wherein the first compressor has a greater number of stages than the first turbine, wherein the second turbine has a greater number of stages than the first turbine, and wherein the second compressor has a greater number of stages than the second turbine;
• a first spool and a second spool, wherein the first spool includes a first shaft interconnecting the first compressor and the second turbine, and the second spool includes a second shaft interconnecting the second compressor and the first turbine;
• wherein an overall pressure ratio is:
• provided by the combination of a pressure ratio across the first compressor and a pressure ratio across the second compressor;
• and
• greater than 40;
• wherein the pressure ratio across the second compressor is no more than 15;
• and
• wherein the pressure ratio across the first compressor is at least 4.