Applied Physics B

, 122:56 | Cite as

High-speed OH* chemiluminescence imaging of ignition through a shock tube end-wall

  • V. A. Troutman
  • C. L. Strand
  • M. F. Campbell
  • A. M. Tulgestke
  • V. A. Miller
  • D. F. Davidson
  • R. K. Hanson


A high-speed OH* chemiluminescence imaging diagnostic was developed to image the structure and homogeneity of combustion events behind reflected shock waves in the Stanford Constrained Reaction Volume Shock Tube. An intensified high-repetition-rate imaging system was used to acquire images of OH* chemiluminescence (near 308 nm) through a fused quartz shock tube end-wall window at 10–33 kHz during the combustion of n-heptane (21 % O\(_{2}\)/Ar, \(\phi = 0.5\)). In general, the imaging technique enabled observation of the main ignition event in the core of the shock tube that corresponded to typical markers of ignition (e.g., pressure rise), as well as localized ignition near the wall that preceded the main core ignition event for some conditions. Case studies were performed to illustrate the utility of this novel imaging diagnostic. First, by comparing localized wall ignition events to the core ignition event, the temperature homogeneity of the post-reflected shock gas near the end-wall was estimated to be within 0.5 % for the test condition presented (\(T=1159\,\hbox {K}, P=0.25\,\hbox {MPa}\)). Second, the effect of a recession in the shock tube wall, created by an observation window, on the combustion event was visualized. Localized ignition was observed near the window, but this disturbance did not propagate to the core of the shock tube before the main ignition event. Third, the effect of shock tube cleanliness was investigated by conducting tests in which the shock tube was not cleaned for multiple consecutive runs. For tests after no cleaning was performed, ignition events were concentrated in the lower half of the shock tube. In contrast, when the shock tube was cleaned, the ignition event was distributed around the entire circumference of the shock tube; validating the cleaning procedure.


Shock Tube Ignition Delay Time Incident Shock Wave Combustion Event Driver Section 
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This material is based upon work supported by the US Army Research Laboratory and the US Army Research Office under Contract/Grant Number W911NF1310206, with Ralph Anthenien as contract monitor. We acknowledge loan of the intensified camera system from an AFOSR-sponsored research program. V.A.T. was supported by the Gabilan Stanford Graduate Fellowship and the National Science Foundation Graduate Research Fellowship Program (Grant No. DGE-114747). Any opinion, findings and conclusions or recommendations expressed in this material are those of the authors(s) and do not necessarily reflect the views of the National Science Foundation. M.F.C. was supported by a National Defense Science and Engineering Graduate Fellowship (32CFR168a).

Supplementary material

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Supplementary material 1 (avi 1150 KB)


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Copyright information

© Springer-Verlag Berlin Heidelberg 2016

Authors and Affiliations

  1. 1.High Temperature Gasdynamics LaboratoryStanford UniversityStanfordUSA
  2. 2.Combustion Research FacilitySandia National LaboratoryLivermoreUSA

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