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

doi:10.1007/s12650-014-0197-2

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 journal › Article › peer-review

32 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 language	English (US)
Pages (from-to)	131-141
Number of pages	11
Journal	Journal of Visualization
Volume	17
Issue number	2
DOIs	https://doi.org/10.1007/s12650-014-0197-2
State	Published - May 2014
Externally published	Yes

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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10.1007/s12650-014-0197-2

Cite this

@article{32f19f6ba9464794b6f0f2ba3adebbab,

title = "OH PLIF visualization of the UVa supersonic combustion experiment: Configuration A",

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.",

keywords = "Flow visualization, Planar laser-induced fluorescence, Supersonic combustion",

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

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{\textquoteright}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.",

year = "2014",

month = may,

doi = "10.1007/s12650-014-0197-2",

language = "English (US)",

volume = "17",

pages = "131--141",

journal = "Journal of Visualization",

issn = "1343-8875",

publisher = "Springer Science and Business Media Deutschland GmbH",

number = "2",

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AU - Johansen, Craig T.

AU - McRae, Colin D.

AU - Danehy, Paul M.

AU - Gallo, Emanuela C.A.

AU - Cantu, Luca M.L.

AU - Magnotti, Gaetano

AU - Cutler, Andrew D.

AU - Rockwell, Robert D.

AU - Goyne, Chris P.

AU - McDaniel, James C.

N1 - 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.

PY - 2014/5

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N2 - 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.

AB - 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.

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ER -

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

Abstract

Bibliographical note

Keywords

ASJC Scopus subject areas

Access to Document

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