Gas turbine engine accessory system
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United States of America Patent
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Sep 1, 2015
Grant Date -
May 6, 2010
app pub date -
Oct 30, 2008
filing date -
Oct 30, 2008
priority date (Note) -
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Abstract
In one embodiment, a gas turbine engine may include an accessory system integrated in a frame between a bypass flow path and a core flow path. A shaft may be provided between the accessory system and a core shaft of the gas turbine engine. The integrated accessory system may include power devices such as motors and generators, among other types of devices. The gas turbine engine may have more than one device spaced at various circumferential locations. In one non-limiting example, two power devices may be spaced 180 degrees apart. In some embodiments, a shaft and gearing may be provided to a location such as a frame in preparation to receive a power device at a later time.
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