Load distribution panel assembly, system and method

Patent metadata

Field	Value
Publication number	US-11022071-B2
Application number	US-201615387620-A
Country	US
Kind code	B2
Filing date	Dec 21, 2016
Priority date	Dec 21, 2016
Publication date	Jun 1, 2021
Grant date	Jun 1, 2021

Abstract

There is provided a load distribution panel assembly for a gas turbine engine. The assembly has a panel structure having at least one circumferential structural panel having a first end, and a second end coupled to a fixed structure of the gas turbine engine. The circumferential structural panel has a first compliant portion extending away from the first end, and has a second stiffened portion angled with respect to and extending radially away from the first compliant portion, and terminating at the second end. The second stiffened portion has a closed stiffened cavity portion integral with a perimeter flange portion. The panel assembly converts fore/aft point load(s) applied to it by load applying apparatus(es), to hoop tension and compression loads, and reacts a load offset in in-plane load(s), to provide uniform load distribution of the fore/aft point load(s) to the fixed structure.

First claim

What is claimed is:

1. A load distribution panel assembly for providing a uniform load distribution in a thrust reverser assembly of an aircraft engine assembly in an aircraft, the load distribution panel assembly comprising:
a fan;
an engine fan case shrouding the fan;
an outer groove fitting formed in the engine fan case;
a panel structure comprising a circumferential structural panel, the circumferential structural panel comprising:
a first end attached to the engine fan case at the outer groove fitting;
a second end located forward of the first end and forming a forward movable edge of the circumferential structural panel;
a compliant barrel portion comprising a first inner surface and a first outer surface, the first inner surface facing the engine fan case and at least partially surrounding the engine fan case; and
a stiffened bulb portion coupled to the compliant barrel portion and forming an acute angle with a line coplanar with the compliant barrel portion,
the compliant barrel portion extending between the first end and the stiffened bulb portion,
the stiffened bulb portion extending radially away from the compliant barrel portion to the second end such that the second end is radially outward of the first end with respect to an engine central axis; and
the stiffened bulb portion comprising a second inner surface and a second outer surface, which is straight, parallel to and offset relative to the second inner surface, such that the second inner surface and the second outer surface form a closed stiffened cavity portion.

2. The load distribution panel assembly of claim 1 , further comprising one or more clevis members, coupled to the second inner surface of the stiffened bulb portion of the circumferential structural panel and configured to couple to one or more thrust reverser actuation system (TRAS) actuators.

3. The load distribution panel assembly of claim 2 , wherein each of the one or more clevis members comprises an attachment hole, engageable to a tie rod of the one or more TRAS actuators.

4. The load distribution panel assembly of claim 2 , wherein the stiffened bulb portion comprises one or more attachment openings, each aligned with a corresponding one of the one or more clevis members and configured to receive a corresponding one of the one or more TRAS actuators.

5. The load distribution panel assembly of claim 1 , wherein the compliant barrel portion and the stiffened bulb portion comprise a single monolithic structure.

6. The load distribution panel assembly of claim 1 , wherein the stiffened bulb portion has 100 (one hundred) times to 1000 (one thousand) times greater stiffness than the compliant barrel portion.

7. The load distribution panel assembly of claim 1 , wherein the stiffened bulb portion comprises a non-quasi isotropic laminate.

8. The load distribution panel assembly of claim 1 , wherein a cross-section of the closed stiffened cavity portion of the stiffened bulb portion has a geometric configuration of a parallelogram, a trapezoid, a rectangle, or an ellipse.

9. The load distribution panel assembly of claim 1 , wherein the second inner surface forms at least a portion of a conical shape.

10. The load distribution panel assembly of claim 1 , wherein the panel structure comprises an additional circumferential structural panel, radially offset relative to the circumferential structural panel.

11. The load distribution panel assembly of claim 1 , wherein the acute angle is between 25° (twenty-five degrees) and 80° (eighty degrees).

12. The load distribution panel assembly of claim 1 , wherein the stiffened bulb portion further comprises a stiffened material, disposed within the closed stiffened cavity portion, and wherein the stiffened material comprises one of a honeycomb core or a foam core.

13. The load distribution panel assembly of claim 1 , wherein the closed stiffened cavity portion of the stiffened bulb portion is hollow.

14. The load distribution panel assembly of claim 1 , wherein the stiffened bulb portion further comprises a perimeter lip portion, extending between the closed stiffened cavity and the second end and forming a portion of the second inner surface.

15. The load distribution panel assembly of claim 1 , wherein the acute angle is between 45° (forty-five degrees) and 60° (sixty degrees).

16. The load distribution panel assembly of claim 1 , wherein the closed stiffened cavity of the stiffened bulb portion extends to the compliant barrel portion.

17. The load distribution panel assembly of claim 1 , wherein each of the second inner surface and the second outer surface of the stiffened bulb portion extends to the compliant barrel portion.

18. The load distribution panel assembly of claim 1 , further comprising an outer blade fitting, attached to the first end of the circumferential structural panel and connected to the outer groove fitting.

Assignees

• Boeing Co

Inventors

• Torjesen Luke D
• Morrow Robert D

Classifications

• B64D29/06

  Attaching of nacelles, fairings or cowlings · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F02K1/72 Primary

  the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• B64D33/04

  of exhaust outlets or jet pipes · CPC title