Gas turbine engine with variable pressure ratio fan system

A multiple bypass turbofan gas turbine engine comprising:

• a fan section, a core engine, and a low pressure turbine in downstream serial flow relationship;
• the core engine including in downstream serial flow relationship a high pressure compressor, a combustor, and a high pressure turbine;
• the high pressure compressor connected in driving engagement to the high pressure turbine blades by a core engine shaft;
• axially spaced-apart first and second stage fans of the engine fan connected in driving engagement to the low pressure turbine by a low pressure shaft;
• a fan bypass duct circumscribing the second stage fan and the core engine;
• a first bypass inlet to the fan bypass duct disposed axially between the first and second stage fans;
• a second bypass inlet to the fan bypass duct axially disposed between the second stage fan and an annular core engine inlet to the core engine;
• first stage fan blades of the first stage fan disposed axially across a first fan duct and second stage fan blades radially disposed axially across a second fan duct;
• the second fan duct located axially aft of the first bypass inlet and disposed radially inwardly of the fan bypass duct;
• a fan shroud dividing the second stage fan blades into radially inner and outer fan hub and tip sections, respectively;
• the tip sections radially disposed in a fan tip duct including an annular duct wall having a non-rotatable forward duct wall portion adjacently forward of the rotatable fan shroud;
• and
• an axially translatable deflector positioned to close the fan tip duct when it opens the first bypass inlet and open the fan tip duct when it closes the first bypass inlet.