GAS TURBINE ENGINE COMPRESSOR ARRANGEMENT

A gas turbine engine (20) includes a fan section (22) that includes a fan (42) with fan blades (43) and thatdrives air along a bypass flow path (B) in a bypass duct (13). A gear reduction (48) is in driving engagement with the fan (42) and has a gear reduction ratio of greater than 3.0 and less than 4.0. A low spool (30) includes a low pressure turbine (46) that drives a low pressure compressor (44) and drives the gear reduction (48) to drive the fan (42) at a speed slower than the low pressure turbine (46). A high spool (32) includes a high pressure turbine (54) that drives a high pressure compressor (52). The high pressure compressor (52) includes a pressure ratio of greater than 6.5 and less than 11.5. A ratio of a product of a pressure ratio of the fan (42) with a pressure ratio of the low pressure compressor (44) pressure to the pressure ratio of the high pressure compressor (52) is greater than 0.35 and less than 0.90. An exhaust gas exit temperature is greater than 900 degrees Fahrenheit (482 °C) and less than 1000 degrees Fahrenheit (538 °C) at maximum take-off.