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  • 1
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    Development of a Premixed Combustion Capability for Scramjet Combustion Experiments (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Hypersonic air-breathing engines rely on scramjet combustion processes, which involve high speed, compressible, and highly turbulent flows. The combustion environment and the turbulent flames at the heart of these engines are difficult to simulate and study in the laboratory under well controlled conditions. Typically, wind-tunnel testing is performed that more closely approximates engine testing rather than a careful investigation of the underlying physics that drives the combustion process. The experiments described in this paper, along with companion data sets being developed separately, aim to isolate the chemical kinetic effects from the fuel-air mixing process in a dual-mode scramjet combustion environment. A unique fuel injection approach is taken that produces a nearly uniform fuel-air mixture at the entrance to the combustor. This approach relies on the precombustion shock train upstream of the dual-mode scramjet combustor. A stable ethylene flame anchored on a cavity flameholder with a uniformly mixed combustor inflow has been achieved in these experiments allowing numerous companion studies involving coherent anti-Stokes Raman scattering (CARS), particle image velocimetry (PIV), and planar laser induced fluorescence (PLIF) to be performed.
    Keywords: Aircraft Propulsion and Power
    Type: NF1676L-20579 , AIAA SciTech 2015; Jan 05, 2015 - Jan 08, 2015; Orlando, FL; United States
    Format: application/pdf
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  • 2
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    Dual-Pump CARS Thermometry and Species Concentration Measurements in a Supersonic Combustor (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The dual-pump coherent anti-Stokes Raman spectroscopy (CARS) method was used to measure temperature and the absolute mole fractions of N2, O2 and H2 in a supersonic combustor. Experiments were conducted in NASA Langley Research Center's Direct Connect Supersonic Combustion Test Facility. In this facility, hydrogen and air bum to increase the enthalpy of the test gas; O2 is then added to simulate air. This gas is expanded through a Mach 2 nozzle and into a combustor model consisting of a short constant-area section followed by a small rearward facing step and another constant area section. At the end of this straight section H2 fuel is then injected at Mach 2 and at 30 deg. angle with respect to the freestream. One wall of the duct then expands at a 3 deg. angle for over 1 meter. The ensuing combustion is monitored optically through ports in the side of the combustor. CARS measurements were performed at the nozzle exit and at four different planes downstream fuel injection. Maps were obtained of the mean temperature, as well as quantitative N2 and O2 and qualitative H2 mean mole fraction fields. Correlations between fluctuations of the different measured parameters are presented for one of the planes of data.
    Keywords: Aircraft Propulsion and Power
    Type: AIAA Paper 2004-0710 , 42nd Aerospace Sciences Meeting and Exhibit; Jan 05, 2004 - Jan 08, 2004; Reno, NV; United States
    Format: text
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  • 3
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    Predicting the Effects of Test Media in Ground-Based Propulsion Testing (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses the progress of work which began in mid-2004 sponsored by the Office of the Secretary of Defense (OSD) Test & Evaluation/Science & Technology (T&E/S&T) Program. The purpose of the work is to improve the state of the art of CFD capabilities for predicting the effects of the test media on the flameholding characteristics in scramjet engines. The program has several components including the development of advance algorithms and models for simulating engine flowpaths as well as a fundamental experimental and diagnostic development effort to support the formulation and validation of the mathematical models. The paper will provide details of current work involving the development of phenomenological models for Reynolds averaged Navier-Stokes codes, large-eddy simulation techniques and reduced-kinetics models. Experiments that will provide data for the modeling efforts will also be described, along with with the associated nonintrusive diagnostics used to collect the data.
    Keywords: Aircraft Propulsion and Power
    Type: 2006 Annual ITEA Technology Review; Aug 07, 2006 - Aug 10, 2006; Cambridge, MA; United States
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  • 4
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    Supersonic Combustion Research at NASA (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper discusses the progress of work to model high-speed supersonic reacting flow. The purpose of the work is to improve the state of the art of CFD capabilities for predicting the flow in high-speed propulsion systems, particularly combustor flowpaths. The program has several components including the development of advanced algorithms and models for simulating engine flowpaths as well as a fundamental experimental and diagnostic development effort to support the formulation and validation of the mathematical models. The paper will provide details of current work on experiments that will provide data for the modeling efforts along with the associated nonintrusive diagnostics used to collect the data from the experimental flowfield. Simulation of a recent experiment to partially validate the accuracy of a combustion code is also described.
    Keywords: Aircraft Propulsion and Power
    Type: 2007 Fall Technical Meeting - Eastern States Section of the Combustion Institute; Oct 21, 2007 - Oct 24, 2007; Charlotesville, VA; United States
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  • 5
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    CARS Temperature and Species Measurements For Air Vehicle Propulsion Systems (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The coherent anti-Stokes Raman spectroscopy (CARS) method has recently been used in the United States and Europe to probe several different types of propulsion systems for air vehicles. At NASA Langley Research Center in the United States, CARS has been used to simultaneously measure temperature and the mole fractions of N2, O2 and H2 in a supersonic combustor, representative of a scramjet engine. At Wright- Patterson Air Force Base in the United States, CARS has been used to simultaneously measure temperature and mole fractions of N2, O2 and CO2, in the exhaust stream of a liquid-fueled, gas-turbine combustor. At ONERA in France and the DLR in Germany researchers have used CARS to measure temperature and species concentrations in cryogenic LOX-H2 rocket combustion chambers. The primary aim of these measurements has been to provide detailed flowfield information for computational fluid dynamics (CFD) code validation.
    Keywords: Aircraft Propulsion and Power
    Type: RTO-MP-AVT-124-Paper 5 , LF99-1354 , RTO/AVT-124 Specialists Meeting on Recent Developments in Non-Intrusive Measurement Technology for Military Application on Model-and Full-Scale Vehicles; Apr 25, 2005 - Apr 29, 2005; Budapest; Hungary
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