Method and apparatus for starting supersonic compressors
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.
- Inventors:
-
- Bellevue, WA
- Issue Date:
- Research Org.:
- National Energy Technology Laboratory (NETL), Pittsburgh, PA, Morgantown, WV (United States)
- Sponsoring Org.:
- USDOE
- OSTI Identifier:
- 1041016
- Patent Number(s):
- 8152439
- Application Number:
- 12/355,702
- 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:
- 47 OTHER INSTRUMENTATION
Citation Formats
Lawlor, Shawn P. Method and apparatus for starting supersonic compressors. United States: N. p., 2012.
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/1041016.
@article{osti_1041016,
title = {Method and apparatus for starting supersonic compressors},
author = {Lawlor, Shawn P},
abstractNote = {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.},
doi = {},
journal = {},
number = ,
volume = ,
place = {United States},
year = {2012},
month = {4}
}
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