ATR guide pins for sliding nacelle

Patent metadata

Field	Value
Publication number	US-9694912-B2
Application number	US-201414187034-A
Country	US
Kind code	B2
Filing date	Feb 21, 2014
Priority date	Feb 22, 2013
Publication date	Jul 4, 2017
Grant date	Jul 4, 2017

Abstract

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 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, 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 when the second annular portion is in the closed position, thereby providing access to the engine core. A guide pin extends forward from the second annular portion. A locking mechanism is disposed within the first annular portion for engaging the guide pin when the second annular portion is in the closed position.

First claim

The invention claimed is:

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:
a cavity configured to receive the guide pin; and
a plurality of collars configured to engage the guide pin;

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.

2. The gas turbine engine nacelle of claim 1 , wherein the front segment and the back segment are conically shaped.

3. The gas turbine engine nacelle of claim 1 , wherein the collars are configured to substantially match a profile of the back segment.

4. The gas turbine engine nacelle of claim 1 , and further comprising a plurality of locking mechanisms configured to engage a plurality of guide pins when the gas turbine engine is in the closed position.

5. A sliding nacelle for a gas turbine engine comprising:
an annular portion coupled to a rail and movable along the rail between a closed position and at least one open position, wherein the annular portion is configured to engage with a fore nacelle having a locking mechanism when the annular portion is in the closed position; and
a guide pin extending forward from the annular portion;
wherein the guide pin comprises a pin shaft with an expansive tip at its free end;
wherein the expansive tip is a spearhead comprising:
a front segment tapered to point toward the fore nacelle; and
a back segment tapered to point toward the annular portion; and

wherein the locking mechanism comprises:
a cavity configured to receive the guide pin; and
a plurality of collars configured to engage the guide pin; 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.

6. The sliding nacelle of claim 5 , wherein the front segment and the back segment are conically shaped.

7. The sliding nacelle of claim 5 , wherein the collars are configured to substantially match a profile of the back segment.

8. The sliding nacelle of claim 5 , and further comprising a plurality of guide pins each configured to engage a locking mechanism of the fore nacelle in the closed position.

Assignees

• United Technologies Corp

Inventors

• Suciu Gabriel L
• Chandler Jesse M

Classifications

• F05D2240/122

  related to the trailing edge of a stator vane · CPC title

• F05D2250/192

  bevelled · CPC title

• F05D2250/294

  grooved · CPC title

• F05D2240/91

  on a stationary structure · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title