Gas fired advanced turbine system. Phase 1, System scoping and feasibility studies

Conference · Mon Nov 01 04:00:00 EST 1993

OSTI ID:10104940

LeCren, R T; White, D J

The basic concept thus derived from the Ericsson cycle is an intercooled, recuperated, and reheated gas turbine. Theoretical performance analyses, however, showed that reheat at high turbine rotor inlet temperatures (TRIT) did not provide significant efficiency gains and that the 50 percent efficiency goal could be met without reheat. Based upon these findings, the engine concept adopted as a starting point for the gas-fired advanced turbine system is an intercooled, recuperated (ICR) gas turbine. It was found that, at inlet temperatures greater than 2450{degrees}F, the thermal efficiency could be maintained above 50%, provided that the turbine cooling flows could be reduced to 7% of the main air flow or lower. This dual and conflicting requirement of increased temperatures and reduced cooling will probably force the abandonment of traditional air cooled turbine parts. Thus, the use of either ceramic materials or non-air cooling fluids has to be considered for the turbine nozzle guide vanes and turbine blades. The use of ceramic components for the proposed engine system is generally preferred because of the potential growth to higher temperatures that is available with such materials.

• Research Organization: Solar Turbines, Inc., San Diego, CA (United States). Research Dept.
• Sponsoring Organization: USDOE, Washington, DC (United States)
• DOE Contract Number: AC21-86MC23166
• OSTI ID: 10104940
• Report Number(s): DOE/MC/23166--94/C0236; CONF-930893--37; ON: DE94003193; BR: AA5505100/AA5510050
• Country of Publication: United States
• Language: English

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