Method and apparatus for starting supersonic compressors
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United States of America Patent
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Apr 10, 2012
Grant Date -
Aug 6, 2009
app pub date -
Jan 16, 2009
filing date -
Jan 18, 2008
priority date (Note) -
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Abstract
A supersonic gas compressor. The compressor includes aerodynamic duct(s) situated on a rotor journaled in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. The convergent inlet is adjacent to a bleed air collector, and during acceleration of the rotor, bypass gas is removed from the convergent inlet via a collector to enable supersonic shock stabilization. Once the oblique shocks are stabilized at a selected inlet relative Mach number and pressure ratio, the bleed of bypass gas from the convergent inlet via the bypass gas collectors is eliminated.
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