Initial Flow Matching Results of MHD Energy Bypass on a Supersonic Turbojet Engine Using the Numerical Propulsion System Simulation (NPSS) Environment

Abstract

Preliminary flow matching has been demonstrated for a MHD energy bypass system on a supersonic turbojet engine. The Numerical Propulsion System Simulation (NPSS) environment was used to perform a thermodynamic cycle analysis to properly match the flows from an inlet to a MHD generator and from the exit of a supersonic turbojet to a MHD accelerator. Working with various operating conditions such as the enthalpy extraction ratio and isentropic efficiency of the MHD generator and MHD accelerator, interfacing studies were conducted between the pre-ionizers, the MHD generator, the turbojet engine, and the MHD accelerator. This paper briefly describes the NPSS environment used in this analysis and describes the NPSS analysis of a supersonic turbojet engine with a MHD generator/accelerator energy bypass system. Results from this study have shown that using MHD energy bypass in the flow path of a supersonic turbojet engine increases the useful Mach number operating range from 0 to 3.0 Mach (not using MHD) to an explored and desired range of 0 to 7.0 Mach. = Mach number at the exit of a component P 0,6 = total pressure at the exit of the MHD accelerator P 6 = static pressure at the exit of the MHD acclerator P elec = power output of the MHD generator P elecA = power input into the MHD accelerator T 0,15 = stagnation temperature at the entrance of the MHD generator T 0,2 = stagnation temperature at the exit of the MHD generator T 0,53 = stagnation temperature at the entrance of the MHD accelerator 1 Aerospace Engineer, Aeropropulsion Division, 21000 Brookpark Rd. MS 5-11, AIAA Senior Member.