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Title: Experimental investigation of a supersonic combustion flowfield employing staged transverse injection behind a rearward-facing step

Abstract

An experimental investigation of a Mach 2 combustor has been conducted in order to characterize flow properties in a supersonic reacting flowfield. Hydrogen was injected transversely as staged, underexpanded jets behind a rearward facing step into a ducted Mach 2 air free stream. The effects of the chemical reaction on the supersonic flowfield was investigated using shadowgraphs, broadband flame emission photography, and planar laser-induced fluorescence of OH. The shadowgraphs indicated a strong affect of the heat release on the wave pattern in the combustor, with a significant increase in flowfield unsteadiness. The broadband flame emission photographs revealed large regions of no combustion in the vicinity of the fuel injectors where fuel/air mixing was insufficient to support combustion. These regions decreased in size as the free stream stagnation temperature was decreased for fixed hydrogen mass flow rate, consistent with an increase in the effective Q-ratio with combustion. The size of the zones containing OH in the planar fluorescence images also both increased as the main flow stagnation temperature was decreased. Reaction zones were found in the planar fluorescence images away from regions containing injectant in a non-reacting study of the same geometry, indicating that the pressure rise associated with the reactionmore » forced a large redistribution of the fuel. 11 refs.« less

Authors:
; ; ; ;  [1]
  1. Florida, University, Gainesville (United States) Virginia, University, Charlottesville (United States)
Publication Date:
Research Org.:
Florida Univ., Gainesville, FL (United States)
OSTI Identifier:
5396396
Report Number(s):
CONF-920157-; AIAA-Paper-92-0090
Resource Type:
Conference
Resource Relation:
Conference: 30. American Institute of Astronautics and Aeronautics (AIAA) aerospace sciences meeting and exhibit, Reno, NV (United States), 6-9 Jan 1992; Other Information: AIAA-Paper--92-0090
Country of Publication:
United States
Language:
English
Subject:
37 INORGANIC, ORGANIC, PHYSICAL AND ANALYTICAL CHEMISTRY; COMBUSTION CHAMBERS; SUPERSONIC FLOW; CHEMICAL REACTIONS; COMBUSTION; FLAMES; FLOW VISUALIZATION; FLUORESCENCE; FUEL-AIR RATIO; HYDROGEN; HYDROXYL RADICALS; IMAGES; MACH NUMBER; STAGNATION; ELEMENTS; FLUID FLOW; LUMINESCENCE; NONMETALS; OXIDATION; RADICALS; THERMOCHEMICAL PROCESSES; VELOCITY; 400800* - Combustion, Pyrolysis, & High-Temperature Chemistry

Citation Formats

Abbitt, III, J D, Segal, C, Mcdaniel, J C, Krauss, R H, and Whitehurst, R B. Experimental investigation of a supersonic combustion flowfield employing staged transverse injection behind a rearward-facing step. United States: N. p., 1992. Web.
Abbitt, III, J D, Segal, C, Mcdaniel, J C, Krauss, R H, & Whitehurst, R B. Experimental investigation of a supersonic combustion flowfield employing staged transverse injection behind a rearward-facing step. United States.
Abbitt, III, J D, Segal, C, Mcdaniel, J C, Krauss, R H, and Whitehurst, R B. 1992. "Experimental investigation of a supersonic combustion flowfield employing staged transverse injection behind a rearward-facing step". United States.
@article{osti_5396396,
title = {Experimental investigation of a supersonic combustion flowfield employing staged transverse injection behind a rearward-facing step},
author = {Abbitt, III, J D and Segal, C and Mcdaniel, J C and Krauss, R H and Whitehurst, R B},
abstractNote = {An experimental investigation of a Mach 2 combustor has been conducted in order to characterize flow properties in a supersonic reacting flowfield. Hydrogen was injected transversely as staged, underexpanded jets behind a rearward facing step into a ducted Mach 2 air free stream. The effects of the chemical reaction on the supersonic flowfield was investigated using shadowgraphs, broadband flame emission photography, and planar laser-induced fluorescence of OH. The shadowgraphs indicated a strong affect of the heat release on the wave pattern in the combustor, with a significant increase in flowfield unsteadiness. The broadband flame emission photographs revealed large regions of no combustion in the vicinity of the fuel injectors where fuel/air mixing was insufficient to support combustion. These regions decreased in size as the free stream stagnation temperature was decreased for fixed hydrogen mass flow rate, consistent with an increase in the effective Q-ratio with combustion. The size of the zones containing OH in the planar fluorescence images also both increased as the main flow stagnation temperature was decreased. Reaction zones were found in the planar fluorescence images away from regions containing injectant in a non-reacting study of the same geometry, indicating that the pressure rise associated with the reaction forced a large redistribution of the fuel. 11 refs.},
doi = {},
url = {https://www.osti.gov/biblio/5396396}, journal = {},
number = ,
volume = ,
place = {United States},
year = {1992},
month = {1}
}

Conference:
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