CONCEPTUAL DESIGN OF AEROPROPULSION ENGINE HEAT EXCHANGERS PART 1: MICRO CHANNELS AND SELECTION OF ADVANCED CONFIGURATIONS

摘要

A major challenge which emerged while looking at approaches for reduction of aviation Greenhouse Gas (GHG) emissions was the design of a core exhaust heat recovery system. As a part of the FAA program under US Department of Transportation Contract Number DTRT57-11-P-80083, an LP Turbine Exhaust Driven (TED-T) secondary cycle was proposed for contrail mitigation as well as an increment of 3% pts. in overall powerplant efficiency. The compact heat exchanger emerged as a critical component for the realization of TED-T. In this work some of the existing advanced compact heat exchanger (HEX) technologies are identified & presented. A 1-D steady state code was developed for heat transfer calculations. A parametric analysis was carried out for the baseline configuration. In this paper, a similar parametric study is presented for an off-set finned HEX operating at the proposed TED-T cycle conditions.