Aircraft Rinse System

Abstract

A method and apparatus for separating particles and dissolved matter from a fluid stream incorporated in an aircraft rinse system. The present invention includes a first pressure source which transports collected rinse fluid into a separator annulus with a filter element disposed therein. The untreated fluid is placed under appropriate pressure sufficient to produce turbulent flow, increased particle kinetics and/or cavitation physics allowing the desired fluid to penetrate and pass into and through the filter media. The filtered fluid is then transported to a collection tank. The contaminant particulate matter retained on the exterior of the filter media may be removed by the instantenous reverse pressurization of the separator annulus by a second pressure source thereby removing the contaminant particles away from contact with the filter media, and which may then be transported to a waste collection tank or a concentrator for further treatment. The treated rinse fluid is thus recycled for use in the aircraft rinse system.

1 . An aircraft rinse system comprising:
 at least one tank for receiving collected rinse water; and   a molecular separator apparatus in fluid communication with said at least one tank, wherein said molecular separator apparatus comprises:   at least one separator with at least one annulus disposed therein;   a flux cartridge with a semi-permeable membrane seated inside said annulus, wherein a fluid ring exists between an interior surface of the annulus and an exterior surface of the flux cartridge;   a first pump in fluid communication with the separator capable of delivering an influent fluid containing at least one contaminant into the separator, wherein the pressure delivered by the first pump provides kinetic energy to the influent fluid to promote turbulent flow within the fluid ring of the separator which results in the retention of contaminant particles on the exterior surface of the flux cartridge and the collection of the filtered fluid within an interior chamber of the flux cartridge; and,   a second pump in fluid communication with the separator capable of reversing the flow of fluid through the flux cartridge, wherein filtered fluid is pumped into the fluid ring from the interior chamber of the flux cartridge which provides for the removal of the contaminant particles from contact with the exterior surface of the flux cartridge and transports a substantial portion of the contaminant particles Out of the separator.   
     
     
         2 . The aircraft rinse system of  claim 1  wherein said at least one tank is a pre-filter holding tank. 
     
     
         3 . The aircraft rinse system of  claim 2 , further comprising:
 a sediment trap separation tank upstream of and in fluid communication with said pre-filter holding tank.   
     
     
         4 . The aircraft rinse system of  claim 2 , further comprising:
 a scum skimming separation tank upstream of and in fluid communication with said pre-filter holding tank.   
     
     
         5 . The aircraft rinse system of  claim 1 , further comprising:
 a post-filter holding tank for receiving treated rinse water from said molecular separator apparatus.   
     
     
         6 . The aircraft rinse system of  claim 5  further comprising:
 at least one pump in fluid communication with said post-filter holding tank; and   a fluid distribution manifold in fluid communication with said at least one pump, said manifold having at least two fluid exit ports.   
     
     
         7 . The aircraft rinse system of claim further comprising:
 a controller for controlling fluid through exit ports of said manifold.   
     
     
         8 . The aircraft rinse system of  claim 7  furthering comprising:
 a fluid nozzle in fluid communication with an exit port.   
     
     
         9 . The aircraft rinse system of  claim 8  wherein said fluid nozzle is directionally adjustable. 
     
     
         10 - 26 . (canceled)