Nacelle with a translatable inlet for an aircraft propulsion system

Patent metadata

Field	Value
Publication number	US-11390393-B2
Application number	US-201916431111-A
Country	US
Kind code	B2
Filing date	Jun 4, 2019
Priority date	Jun 4, 2019
Publication date	Jul 19, 2022
Grant date	Jul 19, 2022

Abstract

A nacelle assembly includes a fixed inlet segment and a translating inlet segment. The translating inlet segment includes a slider beam laterally between a pair of tracks of the fixed inlet segment. The slider beam is mated with and slidable longitudinally along the pair of tracks. The translating inlet segment is configured to translate longitudinally between a retracted position and an extended position. An aft end of the translating inlet segment is abutted against a forward end of the fixed inlet segment when the translating inlet segment is in the retracted position. An airflow inlet into an inlet passage of the nacelle assembly is opened longitudinally between the aft end of the translating inlet segment and the forward end of the fixed inlet segment when the translating inlet segment is in the extended position.

First claim

What is claimed is:

1. A nacelle assembly for an aircraft propulsion system, comprising:
a fixed inlet segment comprising a pair of tracks; and
a translating inlet segment comprising a slider beam laterally between the pair of tracks, the slider beam mated with and slidable longitudinally along the pair of tracks;
the translating inlet segment configured to translate longitudinally between a retracted position and an extended position;
an aft end of the translating inlet segment abutted against a forward end of the fixed inlet segment when the translating inlet segment is in the retracted position;
an airflow inlet into an inlet passage of the nacelle assembly opened longitudinally between the aft end of the translating inlet segment and the forward end of the fixed inlet segment when the translating inlet segment is in the extended position; and
a linear actuator mounted to and extending longitudinally between the fixed inlet segment and the slider beam, the linear actuator configured to translate the translating inlet segment between the retracted position and the extended position;
the linear actuator projecting into a recess in the slider beam such that a mounting connection between the linear actuator and the slider beam is positioned longitudinally forward of an aft end of the slider beam.

2. The nacelle assembly of claim 1 , wherein
the translating inlet segment forms a second airflow inlet into the inlet passage; and
the second airflow inlet is located at a forward end of the translating inlet segment.

3. The nacelle assembly of claim 1 , wherein
the fixed inlet segment further comprises a pair of second tracks; and
the translating inlet segment further comprises a second slider beam laterally between the pair of second tracks, and the second slider beam is mated with and slidable longitudinally along the pair of second tracks.

4. The nacelle assembly of claim 3 , wherein the slider beam and the second slider beam are arranged at opposing sides of the translating inlet segment.

5. The nacelle assembly of claim 1 , wherein the pair of tracks are separated by less than one radian.

6. The nacelle assembly of claim 1 , wherein a lateral width of the slider beam is less than one half of an outer diameter of the nacelle assembly at an interface where the translating inlet segment abuts against the fixed inlet segment.

7. The nacelle assembly of claim 1 , wherein the pair of tracks comprises a C-channel track.

8. The nacelle assembly of claim 1 , wherein
the translating inlet segment is configured with a pair of ribs that extend longitudinally along a centerline of the nacelle assembly; and
the slider beam is positioned laterally between and attached to the pair of ribs.

9. The nacelle assembly of claim 1 , wherein the fixed inlet segment is configured with an access panel for providing access to a mounting connection between the linear actuator and the slider beam when the translating inlet segment is in the retracted position.

10. The nacelle assembly of claim 1 , further comprising a heating element configured at a leading edge of the translating inlet segment.

11. The nacelle assembly of claim 1 , further comprising a heating element configured at a leading edge of the fixed inlet segment.

12. The nacelle assembly of claim 1 , further comprising a heating element configured with the slider beam.

13. A nacelle assembly for an aircraft propulsion system, comprising:
a fixed inlet segment comprising a pair of tracks; and
a translating inlet segment comprising a slider beam laterally between the pair of tracks, the slider beam mated with and slidable longitudinally along the pair of tracks;
the translating inlet segment configured to translate longitudinally along a centerline between a retracted position and an extended position;
an aft end of the translating inlet segment abutted against a forward end of the fixed inlet segment when the translating inlet segment is in the retracted position; and
an airflow inlet into an inlet passage of the nacelle assembly opened longitudinally between the aft end of the translating inlet segment and the forward end of the fixed inlet segment when the translating inlet segment is in the extended position;
wherein the slider beam is configured with an opening that extends radially relative to the centerline through the slider beam and increases an effective area of the airflow inlet.

14. The nacelle assembly of claim 13 , wherein
the slider beam extends laterally between opposing sides of the slider beam; and
a lateral geometry of the slider beam is straight between the opposing sides of the slider beam.

15. The nacelle assembly of claim 13 , wherein
the slider beam extends laterally between opposing sides of the slider beam; and
a lateral geometry of the slider beam is bowed between the opposing sides of the slider beam.

16. The nacelle assembly of claim 13 , further comprising a heating element configured with the slider beam and extending circumferentially about an outer periphery of the opening.

17. A nacelle assembly for an aircraft propulsion system, comprising:
a fixed inlet segment comprising a pair of tracks; and
a translating inlet segment comprising a slider beam laterally between the pair of tracks, the slider beam mated with and slidable longitudinally along the pair of tracks;
the translating inlet segment configured to translate longitudinally between a retracted position and an extended position;
an aft end of the translating inlet segment abutted against a forward end of the fixed inlet segment when the translating inlet segment is in the retracted position; and
an airflow inlet into an inlet passage of the nacelle assembly opened longitudinally between the aft end of the translating inlet segment and the forward end of the fixed inlet segment when the translating inlet segment is in the extended position;
wherein the pair of tracks comprises a first track and a second track; and
wherein the slider beam comprises a mating feature arranged within a channel of the first track, and the mating feature is configured to move longitudinally along the channel.

18. The nacelle assembly of claim 17 , wherein the mating feature comprises a lug arranged within the channel, and the lug extends longitudinally along a side of the slider beam.

Assignees

• Rohr Inc

Inventors

• Cochran Michael

Classifications

• B64D2033/0206

  comprising noise reduction means, e.g. acoustic liners · CPC title

• B64D33/02

  of combustion air intakes · CPC title

• B64D29/06 Primary

  Attaching of nacelles, fairings or cowlings · CPC title

• F02C7/047

  Heating to prevent icing · CPC title

• F05D2250/41

  with one degree of freedom · CPC title