ATR axial V-groove
A gas turbine engine nacelle 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. A rail is coupled to the fore pylon connecting portion and extends in the aft direction from the first annular portion. A second annular portion is positioned aft of the first portion and coupled to the rail. The second 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 with the first annular portion in the closed position, thereby providing access to the engine core. A mating axial groove and rib connection is located between the first annular portion and the second annular portion.
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 portion and coupled to the rail, the second portion being 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 in the closed position, thereby providing access to the engine core;
a mating axial groove and rib connection between the first annular portion and the second annular portion;
a guide pin extending forward from the slidable portion; and
a locking mechanism, disposed within the first annular portion, for engaging the guide pin when the slidable portion is in the closed position.
2. The gas turbine engine nacelle of claim 1 , wherein the axial groove is located on an aft facing surface of the first annular portion, and the rib is located on a forward facing surface of the second annular portion.
3. The gas turbine engine nacelle of claim 1 , wherein the axial groove is located on a forward facing surface of the second annular portion and the rib is located on an aft facing surface of the first annular portion.
4. The gas turbine engine nacelle of claim 1 , wherein the axial groove is substantially v-shaped.
5. The gas turbine engine nacelle of claim 1 , wherein the axial groove forms a continuous circle.
6. The gas turbine engine nacelle of claim 1 , wherein the rib is configured to substantially conform to and mate with the dimensions of the axial groove.
7. A sliding nacelle for a gas turbine engine, the sliding nacelle comprising:
an annular portion coupled to a rail and movable along a centerline between a closed position and at least one open position, wherein the annular portion is configured to engage with an adjacent fore nacelle when the annular portion is in the closed position;
a mating axial groove and rib connection between the annular portion and the fore nacelle;
a guide pin extending forward from the annular portion; and
a locking mechanism, disposed within the fore nacelle, for engaging the guide pin when the annular portion is in the closed position.
8. The sliding nacelle of claim 7 , wherein the axial groove is located on an aft facing surface of the fore nacelle, and the rib is located on a forward facing surface of the annular portion.
9. The sliding nacelle of claim 7 , wherein the axial groove is located on a forward facing surface of the annular portion and the rib is located on an aft facing surface of the fore nacelle.
10. The sliding nacelle of claim 7 , wherein the axial groove is substantially v-shaped.
11. The sliding nacelle of claim 7 , wherein the axial groove forms a continuous circle.
12. The sliding nacelle of claim 7 , wherein the rib is configured to substantially conform to and mate with the dimensions of the axial groove.