Supersonic Magnetohydrodynamic (MHD) Power Generation System and Its Preliminary Experiment
Magneto hydrodynamic (MHD) power generation system has an important potential application in high-speed aero craft. According to the principles of MHD power generation, shock tunnel and ionization, a supersonic MHD power generation system is developed and introduced in this paper. Helium is used for driver gas and argon for driven gas. Equilibrium contact surface operating mode is selected to obtain high temperature, and the K2CO3 powder seed is added into the driven section so that the supersonic flow is electric. When M=2.0 and B=0.5 T, the power generation system is set up to know the experimental conditions. The nozzle entry total pressure is about 0.35 MPa while total temperature about 3965.1 K, and the nozzle exit velocity is calculated 1530.8 m/s. A preliminary experimental investigation is at length carried out by measuring the voltage and current of the segmented MHD power generation channel. Average electrical conductivity is estimated to be 15 S/m approximately. When load factor is 0.5, the maximum power density of this MHD power generation channel is about 2.195 MW/m3, while the maximum value of enthalpy extraction rate tends to be about 0.255%.
Advances in fields of flow and heat transfer control with magnetic field regulated plasma technology
In this paper, the development and application of magnetic field regulated plasma technology in aerospace, industrial manufacturing and other fields are reviewed. A new method to reduce heat transfer and ablation on the inner wall of high temperature gas pipeline by using magnetic field regulated plasma technology is introduced, includes its research status, application prospect and technical problems to be solved. At the same time, the important theories and key technologies which need to be further breakthrough in the application of magnetic field regulated plasma technology in fields of flow and heat transfer control are discussed from the aspects of the mechanism of changing plasma flow and heat transfer characteristics by magnetic field, numerical simulation theory of plasma physical parameters, plasma generation and control technology, magnetic field loading technology and experiment technology.
Advanced Hypersonic Test Facilities
Hypersonic Ground Test Requirements Principles of Hypersonic Test Facility Development NASA's HYPULSE Facility at GASL The LENS I and II Hypervelocity Tunnels and Application to Hypersonic Vehicle Testing Under Fully Duplicated Flight Conditions The U-12 Large Shock Tube Detonation-Driven Shock Tubes and Tunnels Aerothermodynamics Research in the DLR High Enthalpy Shock Tunnel HEG Characteristics of the HIEST and its Applicability for Hypersonic Aerothermodynamic and Scramjet Research Piston Gasdynamic Units with Multicascade Compression Arc-Heated Facilities The SCIROCCO 70-MW Plasma Wind Tunnel Aerodynamic and Propulsion Test Unit Arc-Heated Facilities (LBK) as a Tool to Study Aerothermodynamic Problems of Reentry Vehicles The NASA Langley Research Center 8-ft High Temperature Tunnel NASA Glenn Research Center's Hypersonic Tunnel Facility The ONERA F4 High-Enthalpy Wind Tunnel The AEDC Hypervelocity Wind Tunnel 9 A Hypersonic Ground-Test Facility Using Magnetic Levitation and Electromagnetic Propulsion Recent Increases in Hypersonic Test Capabilities at the Holloman High Speed Test Track and Design of a Magnetically Levitated Test Track Capability Increased Launching Capabilities at AEDC's Range/Track G A New Mach 8-15 True Temperature Test Facility Concept to Meet the U.S. Shortfall in Hypersonic Test Capability New-Generation Hypersonic Adiabatic Compression Facilities with Pressure Multipliers