Patent ID: 9140188
Filing Date: 2015-09-22
Classification: F02C,F02K,Y02T

Abstract:
1. A gas turbine engine comprising: a combustor section; a low spool along an engine axis with a fan section and an intercooling turbine section forward of said combustor section, said fan section and said intercooling turbine section coaxial with said low spool; a high spool along said engine axis with a high pressure compressor section and a high pressure turbine section, said high pressure compressor section and said high pressure turbine section coaxial with said high spool, said high pressure compressor section aft of said intercooling turbine section and forward of said combustor section, said high pressure turbine section aft of said combustor section; and wherein said intercooling turbine section is configured to expand flow between said fan section and an inlet of said high pressure compressor section.