Micro-turbine gas generator and propulsive system

Abstract

A propulsion system includes a first compressor in fluid communication with a fluid source. A first conduit is coupled to the first compressor, and a heat exchanger is in fluid communication with the first compressor via the first conduit. A second conduit is positioned proximal to the heat exchanger. A combustor is in fluid communication with the heat exchanger via the second conduit and is configured to generate a high-temperature gas stream. A third conduit is coupled to the combustor, and a first thrust augmentation device is in fluid communication with the combustor via the third conduit. The heat exchanger is positioned within the gas stream generated by the combustor.

What is claimed is: 
     
         1 . A propulsion system, comprising:
 a first compressor in fluid communication with a fluid source;   a first conduit coupled to the first compressor;   a heat exchanger in fluid communication with the first compressor via the first conduit;   a second conduit positioned proximal to the heat exchanger;   a combustor in fluid communication with the heat exchanger via the second conduit and configured to generate a high-temperature gas stream;   a third conduit coupled to the combustor; and   a first thrust augmentation device in fluid communication with the combustor via the third conduit, the heat exchanger being positioned within the gas stream generated by the combustor.   
     
     
         2 . The propulsion system of  claim 1 , wherein the heat exchanger is disposed within the third conduit. 
     
     
         3 . The propulsion system of  claim 1 , further comprising a turbine coupled to the first compressor and positioned between the combustor and the heat exchanger. 
     
     
         4 . The propulsion system of  claim 3 , wherein the turbine comprises ceramic matrix composites. 
     
     
         5 . The propulsion system of  claim 3 , further comprising a second compressor coupled to the turbine. 
     
     
         6 . The propulsion system of  claim 5 , wherein the turbine is fixedly coupled to the first compressor and is coupled to the second compressor via a clutch. 
     
     
         7 . The propulsion system of  claim 1 , further comprising a swiveling connector coupling the third conduit to the first thrust augmentation device. 
     
     
         8 . The propulsion system of  claim 1 , further comprising a second thrust augmentation device in fluid communication with the combustor. 
     
     
         9 . A combustor, comprising:
 a first toroidal casing circumscribing an axis and having an inlet configured to receive fluid, the first casing defining a first internal chamber in fluid communication with the inlet;   a second toroidal casing disposed within the first internal chamber and circumscribing the axis, the second casing having an outer wall defining a second internal chamber, the outer wall having a plurality of orifices formed therethrough, the orifices providing fluid communication between the first and second chambers;   a plurality of fuel injectors positioned to inject fuel into the second chamber through the orifices; and   outlet structure defining at least one channel in fluid communication with the second chamber, the at least one channel being oriented parallel to the axis.   
     
     
         10 . The combustor of  claim 9 , wherein the orifices are oriented at an oblique angle with respect to the outer wall. 
     
     
         11 . The combustor of  claim 9 , further comprising an ignition source positioned within the second chamber. 
     
     
         12 . The combustor of  claim 9 , wherein the outlet structure comprises an inner wall converging toward the outer wall and is configured to urge high-temperature fluid flowing about the axis within the second chamber through the at least one channel. 
     
     
         13 . The combustor of  claim 9 , further comprising a plurality of funnel elements disposed within the orifices and extending into the second chamber, the funnel elements tapering from the first chamber to the second chamber. 
     
     
         14 . The combustor of  claim 9 , wherein the injectors extending into the second chamber. 
     
     
         15 . The combustor of  claim 9 , wherein the second casing comprises ceramic matrix composites. 
     
     
         16 . The combustor of  claim 9 , further comprising an air source in fluid communication with the inlet, the air source being heated by fluid emitted by the second chamber through the at least one channel.