Method and apparatus for starting supersonic compressors
Abstract
A supersonic gas compressor with bleed gas collectors, and a method of starting the compressor. The compressor includes aerodynamic duct(s) situated for rotary movement in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. A convergent inlet is provided adjacent to a bleed gas collector, and during startup of the compressor, bypass gas is removed from the convergent inlet via the bleed gas 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 effectively eliminated.
- Inventors:
- Issue Date:
- Research Org.:
- Ramgen Power Systems, LLC (Bellevue, WA)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1089421
- Patent Number(s):
- 8500391
- Application Number:
- 13/441,833
- Assignee:
- Ramgen Power Systems, LLC (Bellevue, WA)
- Patent Classifications (CPCs):
-
F - MECHANICAL ENGINEERING F04 - POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS F04D - NON-POSITIVE-DISPLACEMENT PUMPS
- DOE Contract Number:
- FC26-06NT42651
- Resource Type:
- Patent
- Country of Publication:
- United States
- Language:
- English
- Subject:
- 42 ENGINEERING
Citation Formats
Lawlor, Shawn P. Method and apparatus for starting supersonic compressors. United States: N. p., 2013.
Web.
Lawlor, Shawn P. Method and apparatus for starting supersonic compressors. United States.
Lawlor, Shawn P. Tue .
"Method and apparatus for starting supersonic compressors". United States. https://www.osti.gov/servlets/purl/1089421.
@article{osti_1089421,
title = {Method and apparatus for starting supersonic compressors},
author = {Lawlor, Shawn P},
abstractNote = {A supersonic gas compressor with bleed gas collectors, and a method of starting the compressor. The compressor includes aerodynamic duct(s) situated for rotary movement in a casing. The aerodynamic duct(s) generate a plurality of oblique shock waves for efficiently compressing a gas at supersonic conditions. A convergent inlet is provided adjacent to a bleed gas collector, and during startup of the compressor, bypass gas is removed from the convergent inlet via the bleed gas 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 effectively eliminated.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {Tue Aug 06 00:00:00 EDT 2013},
month = {Tue Aug 06 00:00:00 EDT 2013}
}
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