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 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 dual-modal cooling structure can enhance heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.
1. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall tapering to a leading edge, the outer wall comprising a porous section, the porous section comprising a first porous region and a second porous region;
a coolant supply structure defining a first supply flowpath extending to the first porous region and a second supply flowpath extending from the first supply flowpath at a location upstream of the first porous region to the second porous region; and
a coolant supply for providing a flow of a coolant through the coolant supply structure and through the porous section to cool the outer wall.
2. The leading edge assembly of claim 1 , wherein the first porous region is disposed at a stagnation point of the leading edge, wherein the second porous region is disposed immediately adjacent to the first porous region, and wherein the leading edge assembly is configured such that an internal pressure, P 1 , of the coolant as measured at an outermost surface at the first porous region is higher than an internal pressure, P 2 , of the coolant as measured at an outermost surface at the second porous region.
3. The leading edge assembly of claim 1 , wherein the second supply flowpath is configured to recirculate the coolant to an area corresponding with a heat removal device.
4. The leading edge assembly of claim 1 , further comprising one or more barriers disposed between the first and second porous regions.
5. The leading edge assembly of claim 4 , wherein at least one of the one or more barriers is part of a sidewall of the coolant supply structure and defines in part the first supply flowpath, the second supply flowpath, or both.
6. The leading edge assembly of claim 1 , wherein the coolant supply structure further comprises a metering device within the second supply flowpath, and wherein the metering device comprises one or more metering holes disposed in a portion of the coolant supply structure.
7. The leading edge assembly of claim 6 , wherein the one or more metering holes are disposed in a sidewall of the coolant supply structure.
8. The leading edge assembly of claim 1 , wherein the coolant supply structure further comprises one or more impingement devices within the first supply flowpath.
9. The leading edge assembly of claim 1 , wherein the coolant supply structure comprises a variable circulator configured to adjust a pressure of the coolant in the coolant supply structure in response to a detected heat load at one or more portions of the leading edge assembly.
10. The leading edge assembly of claim 1 , wherein the first porous region has a first cross-sectional area, as seen along a plane intersecting the leading edge, wherein the second porous region has a second cross-sectional area, as seen along the plane intersecting the leading edge, and wherein the first cross-sectional area is larger than the second cross-sectional area.
11. The leading edge assembly of claim 1 , wherein the porous section further comprises a third porous region, and wherein the first porous region is disposed between the second porous region and the third porous region, wherein the second and third porous regions have a generally same transpiration rate, and wherein a transpiration rate of the first porous region is higher than the generally same transpiration rate of the second and third porous regions.
12. The leading edge assembly of claim 1 , wherein the second supply flowpath defines an inlet in flow communication with the first supply flowpath.
13. A leading edge assembly for a hypersonic vehicle, the leading edge assembly comprising:
an outer wall tapering to a leading edge, the outer wall comprising a porous section, the porous section comprising a first porous region disposed at a stagnation point of the leading edge and a second porous region disposed adjacent to the first porous region and spaced apart therefrom by a barrier;
a coolant supply structure configured to distribute a coolant from a coolant supply to the porous section, wherein an internal pressure, P 1 , of the coolant in the first porous region is higher than an internal pressure, P 2 , of the coolant in the second porous region as measured at the outer surface.
14. The leading edge assembly of claim 13 , wherein the coolant supply structure comprising a metering device fluidly coupled between the first porous region and the second porous region.
15. The leading edge assembly of claim 13 , wherein the porous section further comprises a third porous region, and wherein the first porous region is disposed between the second porous region and the third porous region.
16. A method of cooling a leading edge assembly for a hypersonic vehicle, the method comprising:
pressurizing a coolant within a coolant supply structure of the leading edge assembly in a direction toward a porous section of the leading edge assembly at a first internal pressure, P 1 , as measured at a leading edge of the porous section; and
adjusting the first internal pressure, P 1 , in response to a changed condition sensed by the leading edge assembly.
17. The method of claim 16 , wherein the porous section includes a first porous region and a second porous region spaced apart from one another by a barrier, wherein the first porous region is disposed at a stagnation point of the leading edge, wherein the second porous region is disposed adjacent to the first porous region, and wherein the first internal pressure, P 1 , of the coolant in the first porous region is higher than a second internal pressure, P 2 , of the coolant in the second porous region.
18. The method of claim 17 , further comprising modulating the internal pressure of at least one of the first and second porous regions in response to a determined heat load at one or more portions of the leading edge assembly.
19. The method of claim 16 , further comprising:
detecting a heat load or interface pressure at one or more portions of the leading edge assembly; and
communicating the detected heat load or interface pressure to a processor configured to modulate pressure of the first internal pressure, P 1 .
20. The method of claim 19 , wherein modulating pressure comprises:
increasing the first internal pressure in response to increased head loads or increased interface pressure; and
decreasing the first internal pressure in response to decreased heat loads or decreased interface pressure.