System and method for cooling a leading edge of a high speed vehicle
A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.
1. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall that is tapered to a forward end;
a porous tip joined to the forward end of the outer wall and extending forward toward a leading edge, the porous tip comprising a first porous region at the leading edge and a second porous region downstream from the leading edge, wherein a first porosity of the first porous region is greater than a second porosity of the second porous region; and
a coolant supply in fluid communication with the porous tip for providing a flow of coolant through the first porous region and the second porous region,
wherein the outer wall comprises a first wall section and a second wall section separated by one or more coolant reservoirs, and
wherein the leading edge assembly further comprises a nose cover positioned at least partially over the porous tip to restrict the flow of coolant within the one or more coolant reservoirs until melted, the nose cover being formed from a material that ablates or melts when the leading edge is exposed to a predetermined critical temperature.
2. The leading edge assembly of claim 1 , wherein the porous tip defines a porosity that progressively increases toward the leading edge.
3. The leading edge assembly of claim 1 , wherein the porous tip defines a radial direction extending from a center of curvature of the porous tip and a circumferential direction, the porous tip comprising a plurality of porous segments spaced apart along the circumferential direction, each of the plurality of porous segments extending from an inner surface of the porous tip to an outer surface of the porous tip.
4. The leading edge assembly of claim 3 , wherein at least two of the plurality of porous segments have different porosities.
5. The leading edge assembly of claim 3 , where a porosity within at least one of the plurality of porous segments varies along the radial direction.
6. The leading edge assembly of claim 1 , wherein the nose cover extends from the first wall section all the way around the porous tip to the second wall section.
7. The leading edge assembly of claim 1 , wherein the nose cover is impermeable by the flow of coolant.
8. The leading edge assembly of claim 1 , further comprising an aft bulkhead, wherein the one or more coolant reservoirs are defined between the aft bulkhead, the first wall section, the second wall section, and the nose cover.
9. The leading edge assembly of claim 8 , wherein the one or more coolant reservoirs have a fixed volume and are charged with the flow of coolant such that a coolant pressure increases as an operating temperature of the leading edge assembly increases.
10. The leading edge assembly of claim 1 , wherein the first wall section and the second wall section are substantially straight, and wherein the porous tip is defined as a curved region joining the first wall section and the second wall section.
11. The leading edge assembly of claim 1 , wherein the flow of coolant comprises at least one of air, water, steam, liquid metal, carbon dioxide, or helium.
12. The leading edge assembly of claim 1 , wherein the coolant supply comprises:
a pump or a capillary system for directing the coolant toward the porous tip.
13. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall that is tapered to a forward end;
a porous tip joined to the forward end of the outer wall and extending forward toward a leading edge, the porous tip comprising a first porous region at the leading edge and a second porous region downstream from the leading edge, wherein a first porosity of the first porous region is greater than a second porosity of the second porous region; and
a coolant supply in fluid communication with the porous tip for providing a flow of coolant through the first porous region and the second porous region,
wherein the porous tip defines a radial direction extending from a center of curvature of the porous tip and a circumferential direction, the porous tip comprising a plurality of porous segments spaced apart along the circumferential direction, each of the plurality of porous segments extending from an inner surface of the porous tip to an outer surface of the porous tip, and
wherein each of the plurality of porous segments are separated by an internal barrier.
14. The leading edge assembly of claim 13 , wherein the internal barrier is straight and extends substantially along the radial direction.
15. The leading edge assembly of claim 13 ,
wherein the outer wall comprises a first wall section and a second wall section separated by one or more coolant reservoirs,
the leading edge assembly further comprising:
a nose cover positioned at least partially over the porous tip to restrict the flow of coolant within the one or more coolant reservoirs until melted, the nose cover being formed from a material that ablates or melts when the leading edge is exposed to a predetermined critical temperature.
16. A porous tip for a leading edge assembly of a hypersonic vehicle, the porous tip defining a radial direction extending from a center of curvature of the porous tip and a circumferential direction, the porous tip comprising:
a plurality of porous segments spaced apart along the circumferential direction, each of the plurality of porous segments extending from an inner surface of the porous tip to an outer surface of the porous tip, wherein at least two of the plurality of porous segments have different porosities;
a plurality of internal barriers, each of the plurality of porous segments being separated from adjacent segments of the plurality of porous segments by at least one of the plurality of internal barriers; and
a nose cover positioned at least partially over the porous tip to restrict a flow of coolant through the porous tip until melted, the nose cover being formed from a material that ablates or melts when the porous tip is exposed to a predetermined critical temperature.
17. The porous tip of claim 16 , wherein a porosity of the plurality of porous segments progressively increases toward a leading edge of the porous tip.
18. The porous tip of claim 16 , wherein a porosity within at least one of the plurality of porous segments varies along the radial direction.
19. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall that is tapered to a forward end;
a porous tip joined to the forward end of the outer wall and extending forward toward a leading edge, the porous tip comprising a plurality of porous regions, each of the plurality of porous regions having a different porosity; and
a coolant supply in fluid communication with the porous tip for providing a flow of coolant through the plurality of porous regions,
wherein the porous tip defines a radial direction extending from a center of curvature of the porous tip and a circumferential direction, the porous tip comprising a plurality of porous segments spaced apart along the circumferential direction, each of the plurality of porous segments extending from an inner surface of the porous tip to an outer surface of the porous tip, and
wherein each of the plurality of porous segments are separated by an internal barrier.