Blocker door assembly having a thermoplastic blocker door for use in a turbine engine

Patent metadata

Field	Value
Publication number	US-11840986-B2
Application number	US-202016857487-A
Country	US
Kind code	B2
Filing date	Apr 24, 2020
Priority date	Aug 29, 2016
Publication date	Dec 12, 2023
Grant date	Dec 12, 2023

Abstract

A blocker door assembly for use in a gas turbine includes a panel, a core integrally formed with the panel, and a plurality of mounting structures extending from at least one of the panel and the core. The plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material.

First claim

What is claimed is:

1. A blocker door assembly for use in a gas turbine engine, the blocker door assembly comprising:
a panel;
a core comprising:
a plurality of cells formed from a first wall having a first thickness and a second wall having a second thickness different from the first thickness, each cell of the plurality of cells defining a single cavity therein; and
a plurality of stiffening ribs, each stiffening rib traversing more than one cell of the plurality of cells; and

a plurality of mounting structures extending from at least one of the panel and the core, wherein the plurality of mounting structures are integrally formed with the core and the panel such that the panel, the core, and the mounting structures are co-molded from a thermoplastic material.

2. The blocker door assembly according to claim 1 , wherein the plurality of stiffening ribs extend a first distance from the panel.

3. The blocker door assembly according to claim 1 , wherein at least one mounting structure comprises a through hole defined therethrough.

4. A method of manufacturing a body portion of the blocker door assembly of claim 1 for use in a gas turbine engine, the method comprising:
forming the panel from a thermoplastic material;
integrally forming the core with the panel from the thermoplastic material; and
co-molding the plurality of mounting structures with the panel and the core from the thermoplastic material.

5. The method according to claim 4 , wherein co-molding the plurality of mounting structures includes causing the thermoplastic material to flow into at least one mounting structure insert, and wherein forming the core comprises pressing at least one core insert into the thermoplastic material.

6. The method according to claim 4 , wherein forming the core comprises forming the plurality of stiffening ribs.

7. The method according to claim 6 , wherein forming the plurality of stiffening ribs comprises forming a first stiffening rib and forming a second stiffening rib obliquely oriented with respect to the first stiffening rib.

8. The method according to claim 6 , wherein forming the plurality of stiffening ribs comprises forming at least one stiffening rib extending from a center of the core toward a corner of the core.

9. A blocker door assembly for use in a gas turbine engine, the blocker door assembly comprising:
a panel;
at least one stiffening rib integrally formed with the panel; and
a plurality of mounting structures extending from at least one of the panel and the at least one stiffening rib, wherein at least one of the plurality of mounting structures is a hinge, and wherein the plurality of mounting structures are integrally formed with the at least one stiffening rib and the panel such that the panel, the at least one stiffening rib, and the mounting structures are co-molded from a thermoplastic material.

10. The blocker door assembly according to claim 9 , further comprising a core, the core comprising a plurality of cells formed from a plurality of walls.

11. The blocker door assembly according to claim 10 , wherein the plurality of walls comprises a first wall having a first thickness and a second wall having a second thickness different from the first thickness.

12. The blocker door assembly according to claim 10 , wherein the plurality of walls comprises a first wall and a second wall obliquely oriented with respect to the first wall.

13. The blocker door assembly according to claim 10 , wherein the plurality of walls comprises at least one wall extending from a center of the core toward a corner of the core.

14. The blocker door assembly according to claim 10 , wherein the plurality of walls comprises a plurality of walls extending from a center of the core toward a corner of the core.

15. The blocker door assembly according to claim 9 , wherein the at least one stiffening rib comprises a plurality of stiffening ribs.

16. The blocker door assembly according to claim 15 , wherein the plurality of stiffening ribs comprises a first stiffening rib having a first thickness and a second stiffening rib having a second thickness.

17. The blocker door assembly according to claim 15 , wherein the plurality of stiffening ribs extend a first distance from the panel.

18. The blocker door assembly according to claim 15 , wherein the plurality of stiffening ribs comprises a first stiffening rib and a second stiffening rib obliquely oriented with respect to the first wall.

19. The blocker door assembly according to claim 15 , wherein the plurality of stiffening ribs comprises at least one stiffening rib extending from a center of the core toward a corner of the core.

Assignees

• Boeing Co

Inventors

• Gaw Kevin O'Brien
• Jones Dylan E
• Larson Michael H
• Shivashankara Belur N
• Grove Randy J
• Barene David John
• Lingelbach Jeston
• Shaffer Kory
• Foutch David W

Classifications

• F02K1/70 Primary

  using thrust reverser flaps or doors mounted on the fan housing · CPC title

• B29C43/18

  incorporating preformed parts or layers, e.g. compression moulding around inserts or for coating articles {(B29C43/206 takes precedence)} · CPC title

• B29C65/02

  by heating, with or without pressure · CPC title

• B29C65/48

  using adhesives {, i.e. using supplementary joining material; solvent bonding} · CPC title

• B29C66/7254

  honeycomb structures · CPC title