High bypass ratio counterrotating turbofan engine

Details High bypass ratio counterrotating turbofan engine High bypass ratio counterrotating turbofan engine

1988-03-10

1988-12-13

Stout, Donald E.

Power plants

Reaction motor

Interrelated reaction motors

60268, 60 39162, 415 65, 416129, F02K 3072

Patent

active

047901330

ABSTRACT:
A gas turbine engine comprising a core gas generator engine for generating combustion gases, an additional power turbine, an additional fan section, and a booster compressor is disclosed. The power turbine includes first and second counterrotatable turbine blade rows effective for rotating first and second drive shafts, respectively. The fan section includes a first fan blade row connected to the first drive shaft and a second fan blade row connected to the second drive shaft. The booster compressor includes a first compressor blade row connected to the first drive shaft and a second compressor blade row connected to the second drive shaft.

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Jet Propulsion Turbojets, by Volney C. Finch (Millbrae, Calif., The National Press, 9/1948, title page, p. iii, and pp. 296 to 304).

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