Geared architecture with inducer for gas turbine engine

A gas turbine engine comprising:

• first and second shafts rotatable about a common axis;
• a first turbine section supported on the first shaft;
• second compressor and turbine sections supported on the second shaft;
• a fan;
• a first compressor section arranged in an axial flow relationship with the second compressor and the first and second turbines;
• a geared architecture operatively connecting the first shaft and the fan, the geared architecture includes first and second gear trains, the first gear train an epicyclic gear train, and the second gear train configured to provide a speed reduction;
• an inducer operative coupled to the gear train;
• a bypass flow path and a core flow path, the first and second compressor and turbine sections arranged in the core flow path, and the fan extending into the bypass flow path, the inducer arranged in the core flow path outside of the bypass flow path and upstream from the first compressor section;
• and
• wherein the first and second shafts respectively provide low and high spools, and the first compressor and turbine sections are low pressure compressor and turbine sections, and the second compressor and turbine sections are high pressure compressor and turbine sections.