High bypass ratio counterrotating gearless front fan engine
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United States of America Patent
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Aug 29, 1989
Issued Date -
N/A
app pub date -
Mar 10, 1988
filing date -
Aug 29, 1986
priority date (Note) -
Expired
status (Latency Note)
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Abstract
A gas turbine engine having a core gas generator engine for generating combustion gases, with an additional power turbine, an additional fan section, and a booster compressor. The power turbine includes two counter rotatable turbine blade rows which are alternately interdigitized and serve to rotate counter rotating first and second drive shafts, respectively. The fan section also includes counter rotating spaced apart fan blade sections which are respectively connected to the first and second drive shafts. A booster compressor is axially positioned between the spaced apart fan sections. The booster compressor likewise includes first and second blade rows which are counter rotating alternately interdigitized and are likewise driven by the first and second drive shafts. The engine is supported from the two frames to permit the nacelle to be non-structural. The core engine is a modular unit so that it can be separable from the counter rotating turbine, fans and booster.
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