VARYING THE BYPASS RATIO OF A TURBOFAN ENGINE
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United States of America Patent
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Issued Date -
Dec 17, 2020
app pub date -
Jun 5, 2020
filing date -
Jun 12, 2019
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Abstract
A variable bypass ratio turbofan engine for an aircraft comprises a high-pressure (HP) spool comprising an HP compressor and a first electric machine driven by an HP turbine, the first electric machine; a low-pressure (LP) spool comprising an LP compressor and a second electric machine driven by an LP turbine; a fan driven by the LP spool and configured to produce a bypass flow for propulsion and a core flow for delivery to the LP compressor, wherein the ratio of the mass flow rates of the bypass flow and the core flow define a bypass ratio; an engine controller configured to, for a fixed thrust setting, control the degree of electrical power generated by one or both of the first electric machine and the second electric machine so as to vary a mass flow rate of the core flow and to thereby vary the bypass ratio of the engine.
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