OH PLIF visualization of the UVa supersonic combustion experiment: Configuration A

Craig T. Johansen, Colin D. McRae*, Paul M. Danehy, Emanuela C.A. Gallo, Luca M.L. Cantu, Gaetano Magnotti, Andrew D. Cutler, Robert D. Rockwell, Chris P. Goyne, James C. McDaniel

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

26 Scopus citations

Abstract

Hydroxyl radical (OH) planar laser-induced fluorescence (PLIF) visualizations were performed in the University of Virginia supersonic combustion experiment. The test section was set up in configuration A, which includes a Mach 2 nozzle, combustor, and extender section. Hydrogen fuel was injected through an unswept compression ramp at two different equivalence ratios. Through the translation of the optical system and the use of two separate camera views, the entire optically accessible range of the combustor was imaged. Single-shot, average, and standard deviation images of the OH PLIF signal are presented at several streamwise locations. The results show the development of a highly turbulent flame structure and provide an experimental database to be used for numerical model assessment.

Original languageEnglish (US)
Pages (from-to)131-141
Number of pages11
JournalJournal of Visualization
Volume17
Issue number2
DOIs
StatePublished - May 2014
Externally publishedYes

Bibliographical note

Funding Information:
Acknowledgments Dr. Johansen was supported by the Natural Sciences and Engineering Research Council of Canada (NSERC). This work was supported by the Air Force Office of Scientific Research (AFOSR) and NASA National Center for Hypersonic Combined Cycle Propulsion grant FA 9550-09-1-0611. The technical monitors are Chiping Li from the AFOSR and Rick Gaffney from NASA.

Funding Information:
Model validation is a significant objective of the University of Virginia’s (UVa) continuous flow, dual-mode supersonic combustion facility (UVaSCF). This facility operates as part of the National Center for Hypersonic Combined Cycle Propulsion program, funded by the Air Force Office of Scientific Research and NASA. The UVaSCF accommodates several flow configurations and can replicate conditions representative of both ramjet and scramjet modes of combustion. Using a series of non-intrusive diagnostics, large amounts of both qualitative and quantitative information can be acquired without perturbing the flow. Through an overlap in the types of data extracted from the different techniques there is redundancy in the data set which is important for credibility. The redundancy also offers information needed to determine the limits of some of the techniques. Measurements using focused schlieren (Rockwell et al. 2012), stereoscopic particle image velocimetry (SPIV) (Rockwell et al. 2012), tunable diode laser absorption spectroscopy (TDLAS) (Goldstein et al. 2011), tunable diode laser absorption tomography (TDLAT) (Busa et al. 2011), coherent anti-Stokes Raman spectroscopy (CARS) (Cutler et al. 2012), and hydroxyl radical (OH) planar laser-induced fluorescence (PLIF) (Johansen et al. 2012) are in the process of being performed in this facility.

Keywords

  • Flow visualization
  • Planar laser-induced fluorescence
  • Supersonic combustion

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Electrical and Electronic Engineering

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