System and method for cooling a leading edge of a high speed vehicle

Patent metadata

Field	Value
Publication number	US-11427330-B2
Application number	US-201916685541-A
Country	US
Kind code	B2
Filing date	Nov 15, 2019
Priority date	Nov 15, 2019
Publication date	Aug 30, 2022
Grant date	Aug 30, 2022

Abstract

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.

First claim

What is claimed is:

1. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall that is tapered to a leading edge, wherein the outer wall at least partially defines a vapor chamber;
a capillary structure positioned on an inner surface of the outer wall within the vapor chamber; and
a thermal energy storage assembly positioned in thermal communication with the vapor chamber,
wherein the vapor chamber comprises a working fluid therein,
wherein the thermal energy storage assembly comprises:
a reservoir wall extending to a leading edge of the energy storage assembly; and
a phase change material encased within the reservoir wall such that the phase change material is fluidly isolated from the working fluid,

wherein the vapor chamber extends between the leading edge of the outer wall and the leading edge of the energy storage assembly, and
wherein the capillary structure is a wick, a porous structure, or a screen that lines the inner surface of the outer wall and an outer surface of the reservoir wall.

2. The leading edge assembly of claim 1 , wherein the phase change material comprises silicon or beryllium.

3. The leading edge assembly of claim 1 , wherein the phase change material has a melting temperature of greater than 1000 degrees Celsius.

4. The leading edge assembly of claim 1 , wherein the phase change material has a latent heat of fusion greater than 300 kJ/kg.

5. The leading edge assembly of claim 1 , wherein the thermal energy storage assembly comprises a first chamber containing a first phase change material having a first melting temperature and a second chamber containing a second phase change material having a second melting temperature.

6. The leading edge assembly of claim 1 , wherein the capillary structure comprises:
at least one liquid bridge that extends away from the reservoir wall toward the outer wall for providing a shorter path to the leading edge relative to the capillary structure.

7. The leading edge assembly of claim 1 , wherein the outer wall, the reservoir wall, and the capillary structure are additively manufactured as a single monolithic component.

8. The leading edge assembly of claim 1 , wherein the reservoir wall is a compliant containment structure that can expand or contract depending on a state of the phase change material.

9. The leading edge assembly of claim 1 , wherein the reservoir wall has a wavy profile.

10. The leading edge assembly of claim 1 , wherein the reservoir wall extends substantially parallel to the outer wall.

11. The leading edge assembly of claim 1 , further comprising:
a plurality of heat exchange fins mounted on an outer surface of the reservoir wall.

12. The leading edge assembly of claim 11 , wherein each of the plurality of heat exchange fins extends in the spanwise direction.

13. The leading edge assembly of claim 1 , wherein the thermal energy storage assembly is positioned proximate an aft bulkhead of the leading edge assembly.

14. The leading edge assembly of claim 1 , wherein the vapor chamber is charged with lithium, sodium, or silver.

15. The leading edge assembly of claim 1 , wherein the outer wall is formed from a ceramic matrix composite, carbon-carbon composite, or refractory material.

16. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall that is tapered to a leading edge, wherein the outer wall at least partially defines a vapor chamber;
a capillary structure positioned on an inner surface of the outer wall within the vapor chamber; and
a thermal energy storage assembly positioned in thermal communication with the vapor chamber,
wherein the vapor chamber comprises a working fluid therein,
wherein the thermal energy storage assembly comprises:
a reservoir wall extending to a leading edge of the energy storage assembly; and
a phase change material encased within the reservoir wall such that the phase change material is fluidly isolated from the working fluid,

wherein the vapor chamber extends between the leading edge of the outer wall and the leading edge of the energy storage assembly, and
wherein the thermal energy storage assembly comprises:
an internal chamber defined by the reservoir wall within the vapor chamber, and
one or more conduction paths extending through the internal chamber.

17. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall that is tapered to a leading edge, wherein the outer wall at least partially defines a vapor chamber;
a capillary structure positioned on an inner surface of the outer wall within the vapor chamber; and
a thermal energy storage assembly positioned within the vapor chamber,
wherein the vapor chamber comprises a working fluid therein,
wherein the thermal energy storage assembly comprises:
a reservoir wall extending to a leading edge of the energy storage assembly; and
a phase change material encased within the reservoir wall such that the phase change material is fluidly isolated from the working fluid, and

wherein the vapor chamber extends between the leading edge of the outer wall and the leading edge of the energy storage assembly.

18. The leading edge assembly of claim 17 , wherein the phase change material comprises silicon or beryllium.

Assignees

• Gen Electric

Inventors

• Rathay Nicholas William
• Natsui Gregory Alexander
• Rush Brian Magann

Classifications

• B64C30/00

  Supersonic type aircraft · CPC title

• B64C1/10

  Bulkheads · CPC title

• F28F21/00

  Constructions of heat-exchange apparatus characterised by the selection of particular materials {(coatings for modifying heat-transfer F28F13/18; coatings for preventing the formation of deposits or corrosion F28F19/02)} · CPC title

• F28D2021/0021

  for aircrafts or cosmonautics · CPC title

• B64C1/38 Primary

  Constructions adapted to reduce effects of aerodynamic or other external heating · CPC title