Compact Transpiration Cooling System.
DEPARTMENT OF THE NAVY WASHINGTON D C
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The patent relates to a transpiration cooling system for dissipating heat loads in sharp edges of flight vehicle structures moving at hypersonic velocities and sharp leading edges of gas turbine blades operation in high temperature environments. The invention comprises a compact plenum formed by a longitudinal coolant passage having a longitudinal porous segment in its wall, the compact plenum passage fitting within the leading edge structure and extending along the leading edge in a direction transverse to the external hot gas flow. Pressurized gaseous coolant, supplied by a remote reservoir or engine compressor thus flows within the compact plenum inside the leading edge structure and also transpires in a forward direction from the compact plenum through the porous segment and into the critically heated forward stagnation line region of the sharp leading edge structure.
- Jet and Gas Turbine Engines