Impact force dispersal assembly for turbine engines and methods of fabricating the same

Patent metadata

Field	Value
Publication number	US-11002294-B2
Application number	US-201615288625-A
Country	US
Kind code	B2
Filing date	Oct 7, 2016
Priority date	Oct 7, 2016
Publication date	May 11, 2021
Grant date	May 11, 2021

Abstract

A composite fan casing for a turbine engine includes a core including a plurality of core layers of reinforcing fiber bonded together with a resin. The core includes a first surface and an opposing second surface. The fan casing also includes a shock dispersion panel coupled to the first surface, wherein the shock dispersion panel is configured to disperse a shock wave caused by an impact on the second surface to prevent separation of the plurality of core layers.

First claim

What is claimed is:

1. An impact force dispersal assembly comprising:
a structural panel comprising a first surface and an opposing second surface; and
a shock dispersion panel coupled to said first surface, the shock dispersion panel comprising a plurality of solid members having a solid exterior and a solid central interior, wherein said shock dispersion panel is configured to disperse a shock wave caused by an impact on said second surface,
wherein the plurality of solid members extend radially outward from the first surface.

2. The assembly in accordance with claim 1 , wherein said shock dispersion panel comprises a sawtooth-shaped cross-section.

3. The assembly in accordance with claim 1 , wherein said plurality of solid members each comprise at least one sidewall oriented within a range of 30 degrees to 80 degrees with respect to said first surface.

4. The assembly in accordance with claim 1 , wherein said shock dispersion panel is formed from a first material and said structural panel is formed from a second material that is the same as the first material.

5. The assembly in accordance with claim 1 , wherein said shock dispersion panel is formed from a first material having a first acoustic impedance and said structural panel is formed from a second material having a second acoustic impedance lower than the first acoustic impedance.

6. The assembly in accordance with claim 1 , wherein said shock dispersion panel is formed from a first material having a first acoustic impedance and said structural panel is formed from a second material having a second acoustic impedance that is the same as the first acoustic impedance.

7. The assembly in accordance with claim 1 , wherein the solid central interior does not include any hollow portions, and wherein the solid members are formed from an alternating arrangement of resin and layers of reinforcing fiber.

8. The assembly in accordance with claim 1 , wherein said structural panel forms a portion of a fan casing for a gas turbine engine.

9. The assembly in accordance with claim 8 , wherein the plurality of solid members each have a triangle cross-section extending radially outward from the fan casing.

10. A composite fan casing for a turbine engine, said fan casing comprising:
a core comprising a plurality of core layers of reinforcing fiber bonded together with a resin, said core comprising an outer surface and an opposing inner surface; and
a shock dispersion panel coupled to said outer surface, the shock dispersion panel comprising a plurality of solid members having a solid exterior and a solid central interior, wherein said shock dispersion panel is configured to disperse a shock wave caused by an impact on said inner surface to prevent separation of said plurality of core layers, and wherein the plurality of solid members extend radially outward from the outer surface.

11. The fan casing in accordance with claim 10 , wherein said shock dispersion panel comprises a plurality of panel layers of reinforcing fiber bonded together with the resin such that said shock dispersion panel and said core are formed from the same material.

12. The fan casing in accordance with claim 10 , wherein the shock dispersion panel is formed from a first material having a first acoustic impedance and the core is formed from a second material having a second acoustic impedance, wherein the first acoustic impedance is higher than the second acoustic impedance.

13. The fan casing in accordance with claim 10 , wherein said plurality of solid members each comprise at least one sidewall oriented within a range of 30 degrees to 80 degrees with respect to said outer surface.

14. The fan casing in accordance with claim 10 , further comprising an impingement panel coupled to said inner surface opposite said shock dispersion panel.

15. A method of assembling a composite fan casing for a turbine engine, said method comprising:
providing a core including a plurality of core layers of reinforcing fiber bonded together with a resin, wherein the core includes a first surface and an opposing second surface; and
coupling a shock dispersion panel to the first surface, the shock dispersion panel comprising a plurality of solid members having a solid exterior and a solid central interior, wherein the shock dispersion panel is configured to disperse a shock wave caused by an impact on the second surface to prevent separation of the plurality of core layers, and wherein the plurality of solid members extend radially outward from the first surface.

16. The method in accordance with claim 15 , wherein coupling a shock dispersion panel to the first surface comprises coupling a shock dispersion panel that includes a plurality of panel layers of reinforcing fiber bonded together with the resin such that the shock dispersion panel and the core are formed from the same material.

17. The method in accordance with claim 15 , wherein coupling a shock dispersion panel to the first surface comprises coupling a shock dispersion panel that includes a sawtooth-shaped cross-section.

18. The fan casing in accordance with claim 10 , wherein the shock dispersion panel is formed from a first material having a first acoustic impedance and the core is formed from a second material having a second acoustic impedance that is the same as the first acoustic impedance, and wherein with the shock wave traveling through the core, the shock wave travels past the outer surface of the core into the shock dispersion panel which disperses the shock wave caused by the impact on the inner surface to prevent separation of the plurality of core layers.

19. The fan casing in accordance with claim 10 , wherein the core is formed from an alternating arrangement of the resin and the plurality of core layers.

20. The fan casing in accordance with claim 19 , wherein the solid central interior does not include any hollow portions, and wherein the solid members are formed from a second alternating arrangement of the resin and the layers of reinforcing fiber.

Assignees

• Gen Electric
• General Electric Comany

Inventors

• Klaassen Richard Eugene

Classifications

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F04D29/403

  especially adapted for elastic fluid pumps · CPC title

• F04D29/522

  especially adapted for elastic fluid pumps · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title