Patent ID: 9239004
Filing Date: 2016-01-19
CPC Classification: F01D,F02C,F02K,F05D

Claim Text:
1. A gas turbine engine comprising: a fan at an axially forward location, said fan rotating about an axis of rotation; said fan delivering air into an outer bypass duct, and across a booster fan positioned radially inwardly of said outer bypass duct, said booster fan delivering air into a radially middle duct, and said booster fan delivering air across a cold turbine section into a radially inner core duct wherein said middle duct is located radially inside of said outer bypass duct and radially outside of said inner core duct; air from said cold turbine section in said inner core duct being directed into a compressor section, and then flowing axially in a direction back toward said fan via a duct located radially inside of said inner core duct through a combustor section, and across a core turbine section, and then being directed into said middle duct; and a gear reduction for driving said fan from a fan drive turbine section.