Geared gas turbine engine arrangement with core split power ratio

A gas turbine engine comprising:

• a propulsor section including a propulsor having a plurality of blades, the propulsor having a low corrected tip speed of less than 1150 ft/sec, and the low corrected tip speed being an actual tip speed divided by [(Tram ° R)/(518.7° R)]{circumflex over ( )}0.5;
• a gear arrangement including a gear reduction ratio greater than 2.6;
• a compressor section including a low pressure compressor and a high pressure compressor, and the high pressure compressor including greater than or equal to 8 stages;
• a turbine section including a low pressure turbine and a high pressure turbine, the high pressure turbine driving the high pressure compressor, the low pressure turbine driving the low pressure compressor and driving the gear arrangement to drive the propulsor, the low pressure turbine including three or more stages, and the low pressure compressor including a greater number of stages than the high pressure turbine;
• wherein the low pressure turbine includes an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5, and the low pressure turbine pressure ratio is pressure measured prior to the inlet as related to pressure at the outlet prior to any exhaust nozzle;
• and
• wherein a core split power ratio is provided by a second power input to the high pressure compressor measured in horsepower divided by a first power input to the low pressure compressor measured in horsepower, the core split power ratio being equal to, or greater than, 1.0 and less than, or equal to, 1.4.