High compression gas turbine with superheat enhancement
OwnerHanford N. Lockwood, Jr.inventor
Life of this patent
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Abstract
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.
Claims15
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.
Dependencies are inferred from the claim text.