There have been many such. Here's one from way back in 1957 for the Brass Bell vehicle.
The primary or load-bearing structure was of aluminum and relied on cooling in a closed-loop arrangement that used water-glycol as the coolant. Wing leading edges had their own closed-loop cooling system that relied on a mix of sodium and potassium metals. Liquid hydrogen, pumped initially to 1,000 pounds per square inch, flowed first through a heat exchanger and cooled the heated water-glycol, then proceeded to a second heat exchanger to cool the hot sodium-potassium. In an alternate design concept, this gas cooled the wing leading edges directly, with no intermediate liquid-metal coolant loop. The warmed hydrogen ran a turbine within an onboard auxiliary power unit and then was exhausted overboard. The leading edges reached a maximum temperature of 1,400ºF, for which Inconel X was a suitable material.
Source: Facing the Heat Barrier: A History of Hypersonics, T. A. Heppenheimer, NASA SP-2007-4232, Part 2 (p. 139) Also viewable here. Part 1 is available here.
Image Source: Report No. D143-945-055 Project Brass Bell, Reconnaissance Aircraft Weapon System, 31-Aug-1957, AD136057 (p. 31)