Supersonic Cooling Nozzle with Airfoils

Abstract

A supersonic cooling system, as disclosed herein, operates by pumping liquid. Because the supersonic cooling system pumps liquid, the cooling system does not require the use of a condenser. The cooling system utilizes a compression wave to facilitate a phase change utilized in the cooling effect generated by the system. An evaporator operates in the critical flow regime in which the pressure in one or more evaporator nozzles will remain almost constant and then ‘shock up’ to the ambient pressure. The evaporator may be provided with airfoils to improve characteristics of the fluid flow, thereby increasing efficiency of the system.

1 . A supersonic cooling system, comprising:
 a pump to facilitate a flow of a fluid through a fluid flow path having both a high pressure and a low pressure region;   an evaporator in the fluid flow path, wherein the fluid accelerates to a velocity that is equal to or greater than the speed of sound; and   at least one airfoil positioned in the evaporator to modify the flow of fluid within the evaporator.   
     
     
         2 . The supersonic cooling system of  claim 1 , wherein a width of the airfoil tapers downward from a thickest portion to a trailing edge so that the airfoil chokes the flow of the fluid at the thickest portion and accelerates the flow along a main body toward the trailing edge. 
     
     
         3 . The supersonic cooling system of  claim 1 , wherein a central body is positioned in the fluid flow path in the evaporator to support multiple airfoils. 
     
     
         4 . The supersonic cooling system of  claim 3 , wherein each of the multiple airfoils further comprises a leading edge, the leading edges of the airfoils choking the flow of the fluid. 
     
     
         5 . The supersonic cooling system of  claim 4 , wherein a width of each airfoil tapers downward from a thickest portion to a trailing edge so that the flow path volume expands from the thickest portions to the trailing edges of the airfoils to accelerate the flow of the fluid. 
     
     
         6 . The supersonic cooling system of  claim 3 , wherein a centerline of the central body is colinear with a centerline of the evaporator to provide a balanced fluid flow path through the airfoils. 
     
     
         7 . The supersonic cooling system of  claim 1 , wherein the airfoil is oriented so that a thickest portion of the airfoil is aligned with a throat of an evaporator nozzle of the evaporator to provide a choke point at or near a leading edge of the airfoil. 
     
     
         8 . The supersonic cooling system of  claim 1 , wherein the evaporator is located in the low pressure region of the fluid flow path, and the evaporator facilitates a phase change of the fluid. 
     
     
         9 . The supersonic cooling system of  claim 1 , wherein fluid flow in the evaporator is in a critical flow regime of the fluid. 
     
     
         10 . The supersonic cooling system of  claim 1 , wherein the system maintains a substantially constant pressure in the fluid flow path in the evaporator, the fluid shocking up to an elevated pressure as the fluid exits the evaporator. 
     
     
         11 . The supersonic cooling system of  claim 10 , wherein the system maintains a substantially constant enthalpy as the fluid shocks up to the elevated pressure. 
     
     
         12 . The supersonic cooling system of  claim 1 , wherein the system maintains a substantially constant enthalpy as the pressure of the fluid is decreased. 
     
     
         13 . The supersonic cooling system of  claim 1 , further comprising a heat exchanger in thermal communication with the fluid. 
     
     
         14 . A supersonic cooling method, comprising:
 pumping a fluid through a fluid flow path, the fluid flow path including an evaporator wherein the fluid flows at a critical flow rate; and   modifying a flow of the fluid with at least one airfoil positioned in the fluid flow path to accelerate the flow of the fluid.   
     
     
         15 . The supersonic cooling method of  claim 14 , wherein the flow of the fluid is modified by multiple airfoils secured to a central body positioned in the fluid flow path in the evaporator. 
     
     
         16 . The supersonic cooling method of  claim 14 , wherein the flow of the fluid is choked by the airfoil. 
     
     
         17 . The supersonic cooling method of  claim 14 , wherein the fluid expands as it travels along portions of a main body between the leading edge and a trailing edge of the airfoil. 
     
     
         18 . The supersonic cooling method of  claim 14 , wherein the evaporator facilitates a phase change of the fluid. 
     
     
         19 . The supersonic cooling method of  claim 14 , wherein the flow of the fluid in the evaporator is accelerated to a velocity equal to or greater than the speed of sound in the fluid. 
     
     
         20 . The supersonic cooling method of  claim 14 , further comprising transferring heat to the fluid via a heat exchanger.