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Development of a nitrous oxide propa...

The University of Alabama in Huntsville.

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Development of a nitrous oxide propane combustor.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Development of a nitrous oxide propane combustor./
作者:	Smith, Nathan William Hardin.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2003,
面頁冊數:	86 p.
附註:	Source: Masters Abstracts International, Volume: 65-02.
Contained By:	Masters Abstracts International65-02.
標題:	Aerospace materials. -
電子資源:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=1413397
ISBN:	9780496181896

Development of a nitrous oxide propane combustor.
Smith, Nathan William Hardin.

Development of a nitrous oxide propane combustor. - Ann Arbor : ProQuest Dissertations & Theses, 2003 - 86 p.

Source: Masters Abstracts International, Volume: 65-02.

Thesis (M.S.E.)--The University of Alabama in Huntsville, 2003.

This item must not be sold to any third party vendors.

This work focuses on the development of a nitrous oxide (N2O)/propane (C3H8) rocket engine. This propellant combination is potentially a high energy alternative to the present space propulsion systems that use hypergolic or cryogenic liquids, or solid propellants. The research was accomplished in two phases. Phase I work resulted in a successful demonstration of the key technologies associated with the development of such a propulsion system. Phase II testing employed a vortex injector with a smaller chamber volume in an effort to stabilize combustion and boost performance. Testing was conducted over a range of mixture ratios from 4 to 8, and characteristic lengths of 12&inches;, 36&inches;, 72&inches;, and 108&inches;. Phase I testing produced promising results with efficiencies near 85%. Instances of low frequency pressure oscillations were observed during Phase I testing. Phase II testing produced repeatable, steady firings over the entire range of mixture ratios with efficiencies near theoretical equilibrium calculations. Alternatives to propane as a fuel should be investigated in order to make this system more attractive for wide spread industrial use and larger applications.

ISBN: 9780496181896Subjects--Topical Terms:

3433227
Aerospace materials.

Development of a nitrous oxide propane combustor.
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500 $a Publisher info.: Dissertation/Thesis.
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506 $a This item must not be sold to any third party vendors.
506 $a This item must not be added to any third party search indexes.
520 $a This work focuses on the development of a nitrous oxide (N2O)/propane (C3H8) rocket engine. This propellant combination is potentially a high energy alternative to the present space propulsion systems that use hypergolic or cryogenic liquids, or solid propellants. The research was accomplished in two phases. Phase I work resulted in a successful demonstration of the key technologies associated with the development of such a propulsion system. Phase II testing employed a vortex injector with a smaller chamber volume in an effort to stabilize combustion and boost performance. Testing was conducted over a range of mixture ratios from 4 to 8, and characteristic lengths of 12&inches;, 36&inches;, 72&inches;, and 108&inches;. Phase I testing produced promising results with efficiencies near 85%. Instances of low frequency pressure oscillations were observed during Phase I testing. Phase II testing produced repeatable, steady firings over the entire range of mixture ratios with efficiencies near theoretical equilibrium calculations. Alternatives to propane as a fuel should be investigated in order to make this system more attractive for wide spread industrial use and larger applications.
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