skip to main content
DOE Patents title logo U.S. Department of Energy
Office of Scientific and Technical Information

Title: 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):
8,500,391
Application Number:
13/441,833
Assignee:
Ramgen Power Systems, LLC (Bellevue, WA)
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 = {2013},
month = {8}
}

Patent:

Save / Share: