Aircraft main engine fuel pump with multiple gear stages using shared journals
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United States of America Patent
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Apr 4, 2017
Grant Date -
Jan 2, 2014
app pub date -
Jun 14, 2013
filing date -
Apr 16, 2009
priority date (Note) -
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Abstract
A multistage gear pump assembly includes first and second gear pumps that use common shafts and are axially separated by a fixed spacer within the housing. Pressurized bearings are provided at opposite axial ends of the first and second gear pumps. The second gear pump handles cruise and idle operations of the aircraft while the first gear pump stage assists in meeting higher demand modes of engine operation. Otherwise, the first gear pump is maintained at a minimal pressure to reduce energy consumption and still provide desired stability and eliminate issues associated with bearing oil whirl associated with prior known arrangements. When additional assistance is required, such as during takeoff, climb, or windmill relight, the first gear pump advantageously contributes to the increased pressure.
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