Abstract/Details

Evaluating combustion instability in a sub-scale combustion experiment with three scaling parameters


2010 2010

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Abstract (summary)

The work explores the use of a laboratory burner to characterize the combustion stability characteristics of a liquid rocket injector at scaled flow conditions. The specific objectives are (1) to match the injector scaled parameters: velocity ratio, momentum ratio, and equivalence ratio; and (2) to evaluate injector combustion stability in a low-pressure, single-element sub-scale combustor. This combustor used gaseous methane and oxygen and a swirl-coaxial injector. A propellant heating system was implemented to match the scaling parameters. The nominal condition, a velocity ratio of 0.646, a momentum ratio of 1.94, and an equivalence ratio of 1.33, produced a 2,350 Hz, 3T mode at 1.19% amplitude. Two dominant instability modes were characterized at the conditions tested, the effects of the scaling parameters studied, and several feed-line instabilities were observed.

Indexing (details)


Subject
Aerospace engineering
Classification
0538: Aerospace engineering
Identifier / keyword
Applied sciences
Title
Evaluating combustion instability in a sub-scale combustion experiment with three scaling parameters
Author
Brooks, John Whitlock
Number of pages
157
Publication year
2010
Degree date
2010
School code
0278
Source
MAI 50/02M, Masters Abstracts International
Place of publication
Ann Arbor
Country of publication
United States
ISBN
9781124909110
Advisor
Frederick, Robert A., Jr.
University/institution
The University of Alabama in Huntsville
University location
United States -- Alabama
Degree
M.S.
Source type
Dissertations & Theses
Language
English
Document type
Dissertation/Thesis
Dissertation/thesis number
1501760
ProQuest document ID
896959521
Copyright
Database copyright ProQuest LLC; ProQuest does not claim copyright in the individual underlying works.
Document URL
http://search.proquest.com/docview/896959521/abstract
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