Split compressor turbine engine

Abstract

A turbine engine includes a first compressor and a second compressor fluidly parallel to the first compressor. A reverse flow combustor is fluidly connected to the first compressor and the second compressor. A first turbine and a second turbine are fluidly connected in series, and fluidly connected to an output of the reverse flow combustor.

The invention claimed is: 
     
       1. A turbine engine comprising:
 a first compressor and a second compressor in fluid parallel with the first compressor, each of the first compressor and the second compressor including multiple compressor stages; 
 a reverse flow combustor fluidly connected to said first compressor and said second compressor; and 
 a first turbine and a second turbine in fluid series, and fluidly connected to an output of the reverse flow combustor. 
 
     
     
       2. The turbine engine of  claim 1 , wherein a fluid inlet of the first compressor and a fluid inlet of the second compressor are equal sized, such that fluid flow into each of the first compressor and the second compressor is equal. 
     
     
       3. The turbine engine of  claim 1 , wherein at least one of said first turbine and said second turbine is a single stage turbine. 
     
     
       4. The turbine engine of  claim 3 , wherein each of said first turbine and said second turbine is a single stage turbine. 
     
     
       5. The turbine engine of  claim 1 , wherein said first compressor and said first turbine are connected to a first spool, and wherein said second compressor and said second turbine are connected to a second spool. 
     
     
       6. The turbine engine of  claim 5 , wherein said first spool and said second spool are collinear. 
     
     
       7. The turbine engine of  claim 1 , wherein said first compressor, said second compressor, said first turbine and said second turbine are connected to a single spool. 
     
     
       8. The turbine engine of  claim 1 , wherein at least one of said first compressor and said second compressor is a direct drive compressor. 
     
     
       9. The turbine engine of  claim 1 , wherein said first compressor and said second compressor are counter-rotating compressors, relative to each other. 
     
     
       10. The turbine engine of  claim 1 , wherein said first compressor and said second compressor are co-rotating. 
     
     
       11. The turbine engine of  claim 1 , wherein at least one of said first compressor and said second compressor is comprised of multiple rotors, each of said rotors being constructed of a lightweight high strength ceramic. 
     
     
       12. The turbine engine of  claim 11 , wherein the lightweight high strength ceramic is a silicon based structural ceramic material. 
     
     
       13. The turbine engine of  claim 12 , wherein the lightweight high strength ceramic comprises one of silicon nitride, silicon carbide, silicon carbide fiber reinforced ceramic composite, and carbon fiber reinforced silicon carbide composite. 
     
     
       14. A method for driving a turbine engine comprising:
 splitting an inlet flow between a first compressor and a second compressor such that the second compressor is in fluid parallel with the first compressor, each of the first compressor and the second compressor including multiple compressor stages; 
 providing an output flow of each of said first compressor and said second compressor to a reverse flow combustor; and 
 driving a first turbine and a second turbine to rotate by expanding combustion products generated in said reverse flow combustor across the first turbine and the second turbine. 
 
     
     
       15. The method of  claim 14 , wherein splitting an inlet flow between the first compressor and the second compressor, comprises splitting the inlet flow evenly. 
     
     
       16. The method of  claim 14 , wherein expanding the combustion products across the first turbine and the second turbine comprises expanding an output of the first turbine across the second turbine. 
     
     
       17. The method of  claim 14 , further comprising driving rotation of the first compressor via a shaft connecting the first compressor to the first turbine, and driving rotation of the second compressor via a shaft connecting the second compressor to the second turbine. 
     
     
       18. The method of  claim 14 , further comprising driving rotation of the first compressor and the second compressor via a shaft connecting the first compressor and the second compressor to the first turbine and the second turbine. 
     
     
       19. A turbine engine comprising:
 a first compressor and a second compressor in fluid parallel with the first compressor, each of the first compressor and the second compressor including multiple compressor stages; 
 a combustor fluidly connected to said first compressor and said second compressor; and 
 a turbine section comprising a first turbine and a second turbine downstream of the first turbine, the turbine section being fluidly connected to an output of the combustor. 
 
     
     
       20. The turbine engine of  claim 19 , wherein each of said first turbine and said second turbine are single stage turbines. 
     
     
       21. The turbine engine of  claim 1 , wherein the first turbine and the second turbine are sized such that the first compressor and the second compressor are driven to rotate at the same speed.