Abstract/Details

Scaling a single element combustor to replicate combustion instability modes of a liquid rocket engine


2010 2010

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Abstract (summary)

This research evaluated a method of scaling a single element sub-scale combustor to match the combustion instability modes of a full-scale liquid rocket engine. The experiments used a shear-coaxial injector in an atmospheric chamber using gaseous oxygen and a heated gaseous methane/nitrogen fuel mixture. The flow conditions matched the full-scale equivalence ratio, propellant velocities and propellant volumetric flow rates. The first set of experiments empirically determined the effect of chamber diameter on chamber temperature. The results were used to calculate the dimensions of the sub-scaled combustion chamber that would match the transverse frequencies of the full-scale engine. The scaled chamber was used in two sets of experiments. The stationary tests placed the injector at the center of the chamber and 0.25 in. from the wall. The centered test displayed evidence of coupling between the 1L chamber mode and the injector oxygen post at 885 Hz. Injector coupling was also observed during experiments with the full-scale rocket engine. With the injector 0.25 in. from the wall, the average chamber temperature dropped about 350°C from the centered test. As a consequence, the frequencies of the transverse modes were lower than the full-scale values. No major difference was found in this research between the stable and unstable set points of the full-scale engine. A translating stage was used to evaluate where various chamber modes appear as a function of injector location. The results show that the 1L chamber mode is present at every location and transverse modes appear as the injector moves near the wall.

Indexing (details)


Subject
Aerospace engineering;
Mechanical engineering
Classification
0538: Aerospace engineering
0548: Mechanical engineering
Identifier / keyword
Applied sciences
Title
Scaling a single element combustor to replicate combustion instability modes of a liquid rocket engine
Author
Sweeney, Brian A.
Number of pages
283
Publication year
2010
Degree date
2010
School code
0278
Source
MAI 49/03M, Masters Abstracts International
Place of publication
Ann Arbor
Country of publication
United States
ISBN
9781124298290
Advisor
Frederick, Robert A., Jr.
University/institution
The University of Alabama in Huntsville
University location
United States -- Alabama
Degree
M.S.E.
Source type
Dissertations & Theses
Language
English
Document type
Dissertation/Thesis
Dissertation/thesis number
1486903
ProQuest document ID
761661327
Copyright
Database copyright ProQuest LLC; ProQuest does not claim copyright in the individual underlying works.
Document URL
http://search.proquest.com/docview/761661327/abstract
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