Patent ID: 9694912
Date: 2017-07-04
CPC Classifications: B64D,F01D,F05D,Y10T

Claim:
1. A gas turbine engine nacelle comprising: a first annular portion that is stationary and adapted for partially surrounding an engine core, the first annular portion including a fore pylon connecting portion; a rail coupled to the fore pylon connecting portion and extending in the aft direction from the first annular portion; a second annular portion, aft of the first annular portion and coupled to the rail, the second annular portion movable along an engine core centerline between a closed position and at least one open position, wherein the second annular portion is configured to engage with the first annular portion when the second annular portion is in the closed position, thereby providing access to the engine core; a guide pin extending forward from the second annular portion; and a locking mechanism, disposed within the first annular portion, for engaging the guide pin when the second annular portion is in the closed position, the locking mechanism comprising: wherein the guide pin comprises a pin shaft with an expansive tip at its free end, the expansive tip forming a spearhead shape; wherein the spearhead comprises a front segment tapered to point toward the first annular portion, and a back segment tapered to point toward the second annular portion; and wherein the plurality of collars is further configured to be movable from a first fully recessed position within the locking mechanism to a second position of engagement with the back segment of the spearhead.