Full ring sliding nacelle with thrust reverser
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United States of America Patent
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Sep 6, 2016
Grant Date -
May 7, 2015
app pub date -
Feb 21, 2014
filing date -
Feb 22, 2013
priority date (Note) -
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Abstract
A gas turbine engine includes a first annular portion that is stationary and adapted for partially surrounding an engine core. The first annular portion includes a fore pylon connecting portion. The gas turbine engine also includes a rail coupled to the fore pylon and extending in the aft direction from the first annular portion. The gas turbine engine also includes a second annular portion, arranged aft of the first portion and coupled to the rail. The second annular portion is movable along an engine core centerline between a closed position and at least one open position. The second annular portion is configured to engage the first annular portion in the closed position, thereby providing access to the engine core. The gas turbine engine further comprises a thrust reverser arranged in the second annular portion.
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