초록 ▼

A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)

A system and method for adding superheat to the hot process gas at the discharge of a compressor drive turbine of a high compression ratio gas turbine or aviation gas turbine. The superheat brings the temperature ratio (T2/T1) of the power output turbine into equality with the pressure ratio (P2/P1)(K-1)/K to effect a highly efficient and adiabatic isentropic expansion across the power output turbine. The added superheat contributes to the output power of the engine less any inefficiency of the output power turbine. All of the variables are brought together to develop the proper superheat levels for obtaining the greatest power output possible at minimum fuel consumption levels.

대표청구항 ▼

What is claimed is: 1. A method for operating a superheat gas turbine comprising at least a compressor unit in direct communication with a primary combustor which in turn is in direct communication and on the same shaft with at least a compressor drive turbine, a power output turbine on a separate

What is claimed is: 1. A method for operating a superheat gas turbine comprising at least a compressor unit in direct communication with a primary combustor which in turn is in direct communication and on the same shaft with at least a compressor drive turbine, a power output turbine on a separate shaft, and a second superheat combustion chamber connected to receive the working gas from the compressor drive turbine, the method comprising: adding sufficient heat to the working gas in the second superheat combustion chamber to bring the temperature ratio across the power output turbine T2/T1 to within 15 percent of the adiabatic isentropic balance with the pressure ratio (P2/P1)(K-1)/K across the same power output turbine. 2. The method of claim 1 wherein the pressure at the outlet of the compressor drive turbine is designed to be at maximum level. 3. The method of claim 1 wherein the combustion is stepped with 75-80 percent of the combustion in the primary combustion chamber and 20-25 percent of combustion is in the superheat combustion chamber. 4. The method of claim 1 further comprising positively controlling the ignition of the fuel in the superheat combustion chamber. 5. The method of claim 1 wherein the specific work (KWH/lb. of air) is greater than 0.045. 6. The method of claim 1 wherein the specific fuel consumption on natural gas (lbs. per hr/HP per hr.) is less than 0.320. 7. The method of claim 1 wherein the specific fuel consumption on light fuel oil (lbs. per hr./HP per hr.) is less than 0.340. 8. The method of claim 1 wherein the increase in temperature during the superheat combustion is 700째 F. or less. 9. The method of claim 1 further comprising igniting the superheat combustion only after the power output shaft is rotating. 10. The method of claim 1 wherein the CO2 produced by burning natural gas divided by the kilowatt hrs. of power produced (lbs. of CO2 per hr./KWH) is 0.047 or less. 11. The method of claim 1 wherein the CO2 produced by burning light fuel oil divided by the kilowatt hrs. of power produced (lbs. of CO2 per hr./KWH) is 0.0715 or less. 12. The method of claim 1 further comprising obtaining additional output power by injecting steam into the superheat combustion process. 13. The method of claim 1 further comprising adding a low pressure compressor to the power output shaft to augment the high pressure compressor. 14. The method of claim 12 wherein water is injected into the working gas and evaporated to cool the working gas entering the high pressure compressor. 15. The method of claim 1 wherein the turbine process gas pressure drop in the superheat combustion chamber is less than 20 inches WC.