Preliminary design and key components validation of modular recuperated micro gas turbine for small unmanned systems

Abstract

This paper presents an overview of the preliminary design of a modular recuperated micro gas turbine for small unmanned systems, demonstrating the technical feasibility of this integrated power solution. Analysis identifies a pressure ratio near 5.0 as optimal and feasible for the high-power scheme, balancing flow-specific power and thermal efficiency. Electrical power outputs between 15 kW and 150 kW are achievable, with specific fuel consumption (SFC) lower than 0.225 kg/(kW∙h) for outputs exceeding 50 kW. At 150 kW point, thermal efficiency for electricity reaches 37.3 % with an SFC of 0.2294 kg/(kW∙h). The low-power scheme achieves 0.78 isentropic efficiency at a pressure ratio of 2.85, with turbine efficiency higher than 0.825. The high-power scheme's compressor achieves an efficiency of 0.798 with a pressure ratio of 5.08, and the turbine efficiency reaches 0.897. Experimental testing of the single-can combustor shows a total pressure loss of 3.29 % and combustion efficiency of 97.13 % at design point. The cross-corrugated primary surface recuperator achieves an effectiveness of 0.9195 and total pressure loss of 3.69 % at a heat-weight ratio of 7.76 kW/kg.

Keywords

• Recuperated micro gas turbine
• Electric vehicle
• Thermodynamic analysis
• Cross-corrugated surface recuperator
• Unmanned system
• Modular design