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Evaluation of Impinging Stream Vortex Chamber Concepts for Liquid Rocket Engine ApplicationsTo pursue technology developments for future launch vehicles, NASA/Marshall Space Flight Center (MSFC) is examining vortex chamber concepts for liquid rocket engine applications. Past studies indicated that the vortex chamber schemes potentially have a number of advantages over conventional chamber methods. Due to the nature of the vortex flow, relatively cooler propellant streams tend to flow along the chamber wall. Hence, the thruster chamber can be operated without the need of any cooling techniques. This vortex flow also creates strong turbulence, which promotes the propellant mixing process. Consequently, the subject chamber concepts not only offer the system simplicity, but they also would enhance the combustion performance. The test results showed that the chamber performance was markedly high even at a low chamber length-to-diameter ratio (L/D). This incentive can be translated to a convenience in the thrust chamber packaging. Variations of the vortex chamber concepts have been introduced in the past few decades. These investigations include an ongoing work at Orbital Technologies Corporation (ORBITEC). By injecting the oxidizer tangentially at the chamber convergence and fuel axially at the chamber head end, Knuth et al. were able to keep the wall relatively cold. A recent investigation of the low L/D vortex chamber concept for gel propellants was conducted by Michaels. He used both triplet (two oxidizer and one fuel orifices) and unlike impinging schemes to inject propellants tangentially along the chamber wall. Michaels called the subject injection scheme as Impinging Stream Vortex Chamber (ISVC). His preliminary tests showed that high performance, with an Isp efficiency of 92%, can be obtained. MSFC and the U.S. Army are jointly investigating an application of the ISVC concept for the cryogenic oxygen/hydrocarbon propellant system. This vortex chamber concept is currently tested with gel propellants at AMCOM at Redstone Arsenal, Alabama. A version of this concept for the liquid oxygen (LOX)/hydrocarbon fuel (RPM) system has been derived from the one for the gel propellant.
Document ID
20020051004
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
Trinh, Huu P.
(NASA Marshall Space Flight Center Huntsville, AL United States)
Bullard, Brad
(NASA Marshall Space Flight Center Huntsville, AL United States)
Kopicz, Charles
(Swedrup Engineering Corp. Huntsville, AL United States)
Michaels, Scott
(Army Missile Command Redstone Arsenal, AL United States)
Turner, James
Date Acquired
August 20, 2013
Publication Date
December 14, 2001
Subject Category
Spacecraft Propulsion And Power
Meeting Information
Meeting: JANNAF CS/APS/PSHS/MSS Joint Meeting
Location: Destin, FL
Country: United States
Start Date: April 8, 2002
End Date: April 12, 2002
Sponsors: Department of the Army, Department of the Navy, Department of the Air Force, NASA Headquarters
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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