Patent ID: 6339927
Filing Date: 2002-01-22
Classification: F02C,F02K

Abstract:
A gas turbine engine, comprising:(a) a combustion chamber; (b) a counter-rotating turbine, completely aft of said combustion chamber, including first and second counter rotatable turbine blade row for rotating first and second concentric drive shafts, respectively; (c) an integrated counter-rotating fan module booster turbocompressor completely forward of said combustion chamber, including a first fan blade row connected to said first drive shaft, and: (i) first and third booster turbocompressor blade rows connected at their hubs to said second drive shaft, connected at their outer circumferences to a shroud disposed coaxially about a center line of said engine and outwardly of said drive shafts, and to which shroud is attached a second fan blade row radially outwards of said shroud; and, (ii) a second booster turbocompressor blade row axially spaced between said first and third booster turbocompressor blade row and connected to said first drive shaft, and (d) a compressor axially positioned between said combustion chamber and said integrated counter-rotating fan module booster turbocompressor, said compressor including a housing, a plurality of compressor stator rows connected to the housing, a plurality of compressor blade rows connected to said second drive shaft such that the first turbine blade row drives said first fan blade row and second booster turbocompressor blade row, wherein said second turbine blade row drives said first and third booster turbocompressor blade rows and said second fan blade row, and the second drive shaft simultaneously drives said plurality of compressor blade rows.