Shaft power transfer in gas turbine engines with machines operable as generators or motors
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United States of America Patent
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Dec 9, 1997
Grant Date -
N/A
app pub date -
Mar 28, 1995
filing date -
Jul 6, 1993
priority date (Note) -
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Abstract
A multispool gas turbine engine for an aircraft application includes a transmission system which is operative to transfer power between relatively rotatable engine spools. In a first mode the transmission system is operative to transfer power from the engine's low pressure spool to its high pressure spool and thereby improve the engine's in-flight relight characteristics; in a second mode it is operative to transfer power from the engine's intermediate pressure spool to its high pressure spool to improve engine part speed performance; and in a third mode to transfer power from the engine's high pressure spool to its intermediate pressure spool to assist in ground starting. With each shaft is an associated flow displacement machine (64,66,62) operable as a pump or motor. In other embodiments, a differential is employed for the power transfer between spools.
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