Numerical simulations of pressure loss mechanism in disk channel
Conference
·
OSTI ID:254656
- Tokyo Institute of Technology (Japan); and others
Three dimensional numerical simulation of a supersonic flow in a disk channel was made to develop a disk MHD generator with high performances. As the first step of the present study, a flow field without MHD effects was treated. Results have shown that wall frictions as well as shock waves induce a large pressure loss for high Mach number flows. It is found also that with an increase of an area ratio(exit/inlet), the stagnation pressure loss at the supersonic region decreases and a flow Mach number is kept high, because effects of the boundary layer becomes smaller. However, a further increase of the area ratio induces a large pressure loss owing to the boundary layer separation. It is confirmed that when a channel height is large, the stagnation pressure loss is decreased and Mach numbers at the supersonic region are kept higher. In addition, a small curvature of the wall between the inlet duct and the supersonic nozzle generates compression waves in the nozzle. Furthermore, thin swirl vanes was proposed. However, tile separation of boundary layer was observed owing to an inappropriate curvature of the vanes. It is suggested that the installation of the swirl vanes could cause a large pressure loss within the nozzle.
- OSTI ID:
- 254656
- Report Number(s):
- CONF-950697--
- Country of Publication:
- United States
- Language:
- English
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