HIGH COMPRESSION GAS TURBINE WITH SUPERHEAT ENHANCEMENT
摘要
HIGH COMPRESSION GAS TURBINE WITH SUPERHEAT ENHANCEMENT 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.
申请公布号
WO2005003533(A2)
申请公布日期
2005.01.13
申请号
WO2004US00282
申请日期
2004.01.07
申请人
HANFORD N. LOCKWOOD, JR.;LOCKWOOD, JR., HANFORD, N.