Patent ID: 7950220
Filing Date: 2011-05-31
Classification: F02C,F02K,F05D

Abstract:
1. A gas turbine engine comprising: a first spool having: a combustor between the at least one compressor blade stage and the at least two turbine blade stage along a core flowpath; at least two additional compressor blade stages interspersed with the first spool at least one compressor blade stage; and a transmission coupling the at least two additional compressor blade stages to the first spool at a fixed ratio for counter-rotation about an engine axis, the blades of at least a stage of the at least two additional blade stages coupled to the transmission inboard and a shroud outboard and unitarily cast or machined with the shroud as a single piece, the blades of at least another of the least two additional blade stages being separately formed from and then mounted to the shroud.