Abstract/Details

Development of a liquid oxygen facility for rocket engine injector performance testing


2010 2010

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Abstract (summary)

This study demonstrated the successful operation of a new liquid oxygen-gaseous methane rocket engine test facility to characterize the performance of a swirl coaxial injector. In support of safe system functional development, an oxygen compatibility and hazards assessment was completed to identify and minimize operational risks. Facility changes were implemented to create a more fault tolerant system. Major upgrades included initiatives to manage the oxygen risk and mitigate specific oxygen ignition mechanisms. Oxygen compatible materials and facility configuration changes were instituted to achieve safer experimentation. The demonstration testing of the cryogenic propellant system employed the swirl coaxial injector element in an ongoing program to study liquid oxygen-methane injectors. The injector performance was evaluated by experimental determination of combustion efficiency. The combustion efficiency determined for the injector arrangement during the single operational test was 80% with a 95% confidence systematic standard uncertainty estimate of 4%. Random uncertainty estimation must await repeated tests.

Indexing (details)


Subject
Aerospace engineering;
Mechanical engineering
Classification
0538: Aerospace engineering
0548: Mechanical engineering
Identifier / keyword
Applied sciences
Title
Development of a liquid oxygen facility for rocket engine injector performance testing
Author
Mulkey, Henry W.
Number of pages
240
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
9781124416649
Advisor
Coleman, Hugh W.
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
1487690
ProQuest document ID
840620406
Copyright
Database copyright ProQuest LLC; ProQuest does not claim copyright in the individual underlying works.
Document URL
http://search.proquest.com/docview/840620406
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