ThreeDimensional Numerical Analyses of Performance Characteristics of Experimental

1
2009-b-45s
Three-Dimensional Numerical Analyses of
Performance Characteristics of Experimental Scale
Scramjet Driven MHD Generator Toru
Takahashi University of Tsukuba
2
Concept of MHD power generation for hypersonic
vehicle
Self-contained combustion-driven MHD power system
Scramjet driven MHD power system
3
Experimental aspect
Experimental-scale Scramjet Combustor
Operating conditions
Magnet
4
Past study
Simulation
Experiment
5
Past study
Simulation
Experiment
6
Objective
To clarify influence of inlet temperature
non-uniformity on generator performance by means
of comparison between results under uniform inlet
temperature condition and non-uniform inlet
temperature condition
To investigate dependence of generator
performance on load condition under non-uniform
inlet temperature condition by means of analyses
with various load conditions
7
Inlet temperature condition
Average 2350 K
Average 2250 K
8
Electrode potential
9
Dependence of generator performance on load
condition
Load current 10 A to 70 A
10
Dependence of electromagnetic field on load
condition
Load current
Generator Region
Nozzle
Nozzle
Load current
Load current
11
Dependence of flow field on load condition
Influence of change in load current on flow field
is a little.
12
Relations of thrust loss and electric power
output to load condition
13
Reason why electric power output has a peak
14
Relation between electric current and power output
Joule dissipation
Work against Lorentz force
15
Reason why thrust loss decreases with increasing
in load current
16
Dependence of x-component of current density on
load current
Nozzle
Nozzle
Generator Region
70 A
10 A
17
Dependence of y-component of current density and
Lorentz force on load current
Nozzle
Generator Region
Nozzle
Law of conservation of current
70 A
10 A
70 A
10 A
18
Conclusion
Electric power output under non-uniform inlet
temperature condition is lower than electric
power output under uniform inlet temperature
condition.
Thrust loss monotonically decreases with
increasing in load current, and electric power
output has a peak to load current.