Supersonic compressors

Claim 1

A SUPERSONIC CENTRIFUGAL FLOW COMPRESSOR FOR A GASEOUS FLUID WHICH COMPRISES A ROTOR TURNING IN ONE DIRECTION, A FIXED DIFFUSER MEMBER COAXIALLY SURROUNDING SAID ROTOR, CENTRIFUGAL BLADES CARRIED BY SAID ROTOR SO AS TO DELIVER AT THEIR TRAILING EDGES FLUID STREAMS FLOWING AT SUPERSONIC VELOCITY AND INCLINED AT ACUTE ANGLES TO THE CIRCULAR PERIPHERY OF SAID ROTOR TURNING IN SAID DIRECTION, AND DIFFUSER BLADES CARRIED BY SAID FIXED MEMBER TO FORM BETWEEN THEM A PLURALITY OF PASSAGES FOR SAID GASEOUS FLUID INCLINED AT OBTUSE ANGLES TO THE CIRCULAR PERIPHERY OF SAID ROTOR TURNING IN SAID DIRECTION, THE FACE OF EACH OF SAID DIFFUSER BLADES THAT IS TURNED TOWARD THE AXIS OF SAID ROTOR HAVING, FROM THE LEADING EDGE THEREOF TO AN INTERMEDIATE POINT OF THE CORRESPONDING PASSAGE, AN AREA IN THE FORM OF A CONCAVE SPIRAL ARC TO PRODUCE RECOMPRESSION WAVES DIRECTED TOWARD SAID ROTOR, THE END OF SAID SPIRAL ARC CORRESPONDING TO THE LAST RECOMPRESSION WAVE CAPABLE OF REACHING SAID ROTOR WITHOUT BEING STOPPED BY THE LEADING EDGE OF THE NEXT DIFFUSER BLADE, THE FORE PORTION OF EACH OF SAID PASSAGES BEING CONVERGENT AND THE REAR PORTION DIVERGENT IN THE DIRECTION OF THE GASEOUS FLUID FLOW, WITH A THROAT BETWEEN SAID PORTIONS, SO AS TO PRODUCE A NORMAL SHOCK WAVE REARWARDLY OF SAID CONVERGENT PORTION, DOWNSTREAM OF WHICH SHOCK VALVE THE FLUID FLOW IS SUBSONIC, THE ABOVE MENTIONED FACE OF EACH OF SAID DIFFUSER BLADES COMPRISING, AFTER SAID SPIRAL ARC AREA, A CONVEX AREA EXTENDING FROM SAID CONCAVE AREA TOWARD SAID THROAT, SAID CONCAVE AND CONVEX AREAS BEING ARRANGED TO PRODUCE, IN SAID CONVERGENT PORTION OF SAID PASSAGE, A SUCCESSION OF EXPANSION WAVES CREATING AN ACCELERATION OF THE GASEOUS FLUID FLOWING PAST THEM TO REACH SAID THROAT, SAID CONVEX AREA BEGINNING AT THE POINT FROM WHICH AN EXPANSION WAVE STARTING FROM SAID LAST MEMTIONED FACE TURNED TOWARD THE AXIS OF SAID ROTOR REACHES THE LEADING EDGE OF THE NEXT BLADE FACING SAID LAST MEMTIONED FACE.