Gas turbine engine

Abstract

A gas turbine engine for highly efficient fuel consumption includes as elements a rotor, a stator and a spindle. The rotor includes a system of passageways, a combustion chamber, and a plurality of exhaust ports. The system of passageways comprises a plurality of axial passageways and radial passageways configured to receive a precombustion air-fuel mixture and transport the precombustion air-fuel mixture to the combustion chamber. The exhaust ports provide fluid communication of postcombustion gas between the combustion chamber and the exterior of the rotor.

1 . A gas turbine engine for highly efficient fuel consumption, comprising:
 a rotor, a stator and a spindle;   the rotor including a system of passageways, a combustion chamber, and a plurality of exhaust ports;   the system of passageways comprises one or more axial and radial passageways configured to receive a precombustion air-fuel mixture and transport the precombustion air-fuel mixture to the combustion chamber;   the plurality of exhaust ports providing fluid communication of a postcombustion gas between the combustion chamber and an exterior of the rotor.   
   
   
       2 . The gas turbine engine according to  claim 1 , wherein the stator and the spindle are a unitary piece. 
   
   
       3 . The gas turbine engine according to  claim 1 , wherein the stator is configured to receive a fuel and transmit the precombustion air-fuel mixture to the rotor. 
   
   
       4 . The gas turbine engine according to  claim 1 , wherein the system of passageways further includes an inlet passageway configured to receive the precombustion air-fuel mixture, and a splitter located such that the precombustion air-fuel mixture passing through the inlet passageway comes into contact with the splitter, divides and moves into and through the axial and radial passageways. 
   
   
       5 . The gas turbine engine according to  claim 3 , wherein the splitter directs fluid equally into the axial and radial passageways. 
   
   
       6 . The gas turbine engine according to  claim 1 , wherein the combustion chamber is defined by one or more chamber walls and a combustion chamber inlet, wherein the combustion chamber inlet comprises the distal end of the axial passageway, the distal end of the radial passageway, a first flange and a second flange. 
   
   
       7 . The gas turbine engine according to  claim 1 , wherein the exhaust ports are defined by substantially circular or substantially rectangular apertures. 
   
   
       8 . The gas turbine engine according to  claim 1 , wherein the exhaust ports define deLaval nozzles. 
   
   
       9 . The gas turbine engine according to  claim 1 , further comprising an ignition source or sources positioned in the combustion chamber. 
   
   
       10 . The gas turbine engine according to  claim 9 , wherein the stator comprises a system for providing electrical power to the ignition source. 
   
   
       11 . The gas turbine engine according to  claim 1 , wherein each exhaust port is defined by one or more exhaust port walls, the exhaust port walls further comprising a convergent wall portion and a divergent wall portion. 
   
   
       12 . The gas turbine engine according to  claim 11 , wherein the convergent wall portion and the divergent wall portion meet at a rounded substantially middle location within the port. 
   
   
       13 . The gas turbine engine according to  claim 1 , having three or more exhaust ports. 
   
   
       14 . The gas turbine engine according to  claim 13 , wherein the three or more exhaust ports are positioned at substantially equal angular separation. 
   
   
       15 . The gas turbine engine according to  claim 1 , wherein the plurality of exhaust ports each have an exhaust port central axis positioned at an offset angle relative to a radial line beginning at the center of said spindle and extending radially. 
   
   
       16 . The gas turbine engine according to  claim 1 , wherein the axial passageways and the radial passageways are positioned proximate the combustion chamber such that heat exchange occurs between said passageways and said combustion chamber through the forward and aft chamber walls. 
   
   
       17 . The gas turbine engine according to  claim 1 , wherein the combustion chamber is configured to receive a coolant at one or more points along the perimeter of the combustion chamber. 
   
   
       18 . A gas turbine engine assembly for receiving and combusting a precombustion air-fuel mixture, comprising:
 a spindle;   a rotatable housing positioned on the spindle;   a combustion chamber defined by the rotatable housing;   wherein the rotatable housing defines one or more axial passageways and one or more radial passageways, the axial passageways configured to receive precombustion air-fuel mixture and transport the precombustion air-fuel mixture past a first flange and into the combustion chamber, said radial passageway configured to receive precombustion air-fuel mixture and transport said precombustion air-fuel mixture past a second flange and into the combustion chamber.   
   
   
       19 . The gas turbine engine according to  claim 18 , wherein the rotatable housing further comprises an inlet passageway and a splitter, the inlet passageway configured to receive precombustion air-fuel mixture, the splitter configured to divide and direct the precombustion air-fuel mixture down the axial and radial passageways in approximately equal portions. 
   
   
       20 . The gas turbine engine according to  claim 18 , wherein the one or more axial passageways comprise a series of a plurality of passageways extending axially along the combustion chamber, and where the series encircles the spindle. 
   
   
       21 . The gas turbine engine according to  claim 18 , wherein the one or more radial passageways comprise a series of a plurality of passageways extending radially outwardly along the combustion chamber, and wherein the series encircles the spindle and at least a portion of the combustion chamber. 
   
   
       22 . The gas turbine engine according to  claim 18 , wherein the one or more axial passageways comprise a single continuous passageway encircling the spindle. 
   
   
       23 . The gas turbine engine according to  claim 18 , wherein the one or more radial passageways comprise a single continuous passageway extending radially and encircling at least a portion of the combustion chamber.