Cooling scheme for scramjet variable geometry hardware
View Patent ↗A cooling system for use in an engine having an element to be cooled includes at least one cooling channel on a first side of the element, at least one cooling channel on a second side of the element, and the at least one cooling channel on the first side communicating with the at least one channel on the second side in a nose region of the element so as to form a cooling circuit. The cooling system has particular utility in cooling interior and exterior surfaces of a movable cowl inlet flap used in a scramjet engine.
1. A scramjet engine comprising:
a movable cowl inlet flap having an actively cooled internal panel and an actively cooled external panel;
each of said internal panel and said external panel having at least one cooling channel;
a torque tube forming a structural component of said flap;
a first manifold within said torque tube for supplying coolant to said at least one cooling channel in said internal panel; and
a second manifold within said torque tube for collecting coolant from said at least one cooling channel in said external panel.
2. A scramjet engine according to claim 1 , wherein said first manifold is separated from said second manifold by a partition wall.
3. A scramjet engine according to claim 2 , further comprising a transverse fluid channel within said partition wall and said fluid channel being in fluid communication with said first manifold via a plurality of distribution holes.
4. A scramjet engine according to claim 3 , further comprising a first blind hole in said partition wall and a coolant inlet fitting positioned within said first blind hole so that fluid entering through said fitting can flow into said fluid channel.
5. A scramjet engine according to claim 4 , further comprising a second blind hole in said partition wall and a coolant exit fitting positioned within said second blind hole, which coolant exit fitting is in fluid communication with said second manifold.
6. A scramjet engine according to claim 5 , wherein said coolant inlet fitting and said coolant exit fitting are positioned at the same radial angle.
7. A scramjet engine according to claim 1 , wherein said flap has a nose region and a plurality of transfer holes positioned within said nose region to allow coolant from said at least one cooling channel in said internal panel to flow into said at least one cooling channel in said external panel.
8. A scramjet engine according to claim 1 , wherein said flap has a leading edge formed from a passively cooled composite structure.
9. A scramjet engine according to claim 1 , further comprising torque arms for imparting movement to said flap.
10. A movable flap element for a scramjet comprising:
an actively cooled internal panel and an actively cooled external panel;
each of said internal panel and said external panel having at least one cooling channel;
a torque tube forming a structural component of said flap;
a first manifold within said torque tube for supplying coolant to said at least one cooling channel in said internal panel; and
a second manifold within said torque tube for collecting coolant from said at least one cooling channel in said external panel.
11. A movable flap element according to claim 10 , further comprising said first manifold being separated from said second manifold by a partition wall.
12. A movable flap element according to claim 11 , further comprising a transverse fluid channel within said partition wall and said fluid channel being in fluid communication with said first manifold via a plurality of distribution holes.
13. A movable flap element according to claim 12 , further comprising a first blind hole in said partition wall and a coolant inlet fitting positioned within said first blind hole so that fluid entering through said fitting can flow into said fluid channel.
14. A movable flap element according to claim 13 , further comprising a second blind hole in said partition wall and a coolant exit fitting positioned within said second blind hole, which coolant exit fitting is in fluid communication with said second manifold.
15. A movable flap element according to claim 14 , wherein said coolant inlet fitting and said coolant exit fitting are positioned at the same radial angle.
16. A movable flap element according to claim 10 , wherein said flap element has a nose region and a plurality of transfer holes positioned within said nose region to allow coolant from said at least one cooling channel in said internal panel to flow into said at least one cooling channel in said external panel.
17. A movable flap element according to claim 10 , wherein said flap element has a leading edge formed from a passively cooled composite structure.
18. A movable flap element according to claim 10 , further comprising said torque tube having opposed outer ends, and caps welded to said torque tube for forming sidewalls for said first and second manifolds.
19. A movable flap element according to claim 18 , wherein each said cap is positioned inboard of a respective one of said outer ends so as to form a space for allowing installation of a plurality of torque arms for imparting movement to said flap element.
20. A movable flap element according to claim 10 , wherein each of said panels has a plurality of outermost channels and said torque tube has a plurality of feed holes for communicating with said outermost channels.