Gas turbine engine with high speed low pressure turbine section

A gas turbine engine comprising:

• a fan including fan blades, and an outer housing that surrounds said fan to define a bypass flow path;
• a bypass ratio greater than 10 and less than 22 at a cruise condition;
• a compressor section in fluid communication with said fan, said compressor section including a first compressor section and a second compressor section;
• a combustion section in fluid communication with said compressor section;
• a turbine section in fluid communication with said combustion section;
• wherein the turbine section includes a first turbine section driving said fan and said first compressor section and a second turbine section driving said second compressor section and a second compressor rotor;
• wherein said first turbine section has a first exit area at a first exit point and rotates at a first speed;
• wherein said second turbine section has a second exit area at a second exit point and rotates at a second speed, which is higher than said first speed;
• wherein a first performance quantity is defined as a product of the first speed squared and said first area;
• wherein a second performance quantity is defined as a product of the second speed squared and said second exit area;
• wherein a performance ratio of said first performance quantity to said second performance quantity is between 0.2 and 0.8;
• and
• wherein a gear reduction is included between said first turbine section and said first compressor section, such that said first compressor section and said fan rotate at a lower speed than said first turbine section.