Patent ID: 8104265
Filing Date: 2012-01-31
Classification: F02C,F02K,F05D

Abstract:
1. A gas turbine comprising: a first gas flow path; a second gas flow path located radially outwardly from the first gas flow path; a third gas flow path located radially outwardly from the second gas flow path; and in series order, an auxiliary fan, a multi-stage fan, a high pressure compressor, a combustion section and a high pressure turbine; the auxiliary fan being operative to provide thrust along the third gas flow path without providing thrust along the first gas flow path or the second gas flow path; the multi-stage fan being located upstream of a location of divergence of the first gas flow path and the second gas flow path; the combustion section and the high pressure turbine being positioned along the first gas flow path the high pressure compressor has a first set of high pressure compressor blades and a second set of high pressure compressor blades; radially outboard portions of the first set of high pressure compressor blades are positioned along the second gas flow path; the second set of high pressure compressor blades and radially inboard portions of the first set of high pressure compressor blades are positioned along the first gas flow path.