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US 4,047,682 AGranted
Fan cowl translation lock
AssigneeRolls-Royce (1971) Limited
InventorFrank Denison Brownhill
Life of this patent
Estimating the term…
Abstract
A gas turbine engine cowl has a portion which translates axially of the remainder, to open or close a reverser gas flow gap. A yoke is attached to the fixed cowl upstream of the gap which yoke is engageable with a member on the translating cowl portion, by dropping thereover as the cowl portion closes the gap. Translation of the cowl portion actuates an abutment via a cam mechanism to release the yoke at such a time as to prevent the yoke dropping too soon, which would result in the cowl portion being unlocked.
Claims5
A gas turbine engine cowl structure comprising:
- a first cowl part;
- a second cowl part, said second cowl part being translatable axially of and relative to said first cowl part to open or close a gap;
- a latch operable to engage said second cowl part to prevent relative translation of said first cowl part and said second cowl part to open the gap;
- and
- latch operation delaying means comprising a movable latch abutment member which in one position abuts said latch to prevent said latch from engaging said second cowl part, said abutment member being mounted on a rotary member, said rotary member comprising a tube having a slot in one side thereof with one end of the slot formed into a cam surface, cam surface engaging means for engaging said slot and for causing rotation of said tube when engaging the cam surface of said slot, said cam surface engaging means engaging said cam surface immediately prior to termination of relative translation of said first cowl part and said second cowl part when closing the gap to cause rotation of said tube with said abutment member clearing said latch whereby said latch can move into engagement with said second cowl part.
2 more elements
Dependencies are inferred from the claim text.