| Abstract: | The possibility of generating electric power in a plane model of an integral high-speed hydrogen-burning jet engine by mounting
a magnetogasdynamic (MHD) generator at the combustion chamber exit is discussed. Attention is concentrated on clarifying the
effect of MHD energy extraction from the stream on the aircraft’s thrust characteristics. The internal and external flows
are simulated numerically. The two-dimensional supersonic gasdynamic flow inside the engine (in the air-intake, combustion
chamber, MHD generator, and nozzle) and the supersonic flow past the aircraft are described on the basis of the complete averaged
system of Navier-Stokes equations (in the presence of turbulence), which includes MHD force and heat sources, a one-parameter
turbulence model, the electrodynamic equations for an ideal segmented MHD generator, and the equations of the detailed chemical
kinetics of hydrogen burning in air. The numerical solution is obtained by means of a computer program that uses a relaxation
scheme and an implicit higher-order version of the Godunov method. It is shown that MHD electric power generation can be realized
without disturbing the positive balance in the relation between the thrust and the drag of the aircraft with the engine operating
with allowance for the MHD drag, but with some loss of effective thrust. |
