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Scramjet operability range studies o...

Bonanos, Aristides M.

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Scramjet operability range studies of an integrated aerodynamic-ramp-injector/plasma-torch igniter with hydrogen and hydrocarbon fuels.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Scramjet operability range studies of an integrated aerodynamic-ramp-injector/plasma-torch igniter with hydrogen and hydrocarbon fuels./
Author:	Bonanos, Aristides M.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2005,
Description:	116 p.
Notes:	Source: Dissertations Abstracts International, Volume: 67-08, Section: B.
Contained By:	Dissertations Abstracts International67-08B.
Subject:	Aerospace materials. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3191731
ISBN:	9780542338984

Scramjet operability range studies of an integrated aerodynamic-ramp-injector/plasma-torch igniter with hydrogen and hydrocarbon fuels.
Bonanos, Aristides M.

Scramjet operability range studies of an integrated aerodynamic-ramp-injector/plasma-torch igniter with hydrogen and hydrocarbon fuels. - Ann Arbor : ProQuest Dissertations & Theses, 2005 - 116 p.

Source: Dissertations Abstracts International, Volume: 67-08, Section: B.

Thesis (Ph.D.)--Virginia Polytechnic Institute and State University, 2005.

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

An integrated aerodynamic-ramp-injector/plasma-torch-igniter of original design was tested in a M∞ = 2, unvitiated, heated flow facility arranged as a diverging duct scramjet combustor. The facility operated at a total temperature of 1000 K and total pressure of 330 kPa. Hydrogen (H 2), ethylene (C2H4) and methane (CH4) were used as fuels, and a wide range of global equivalence ratios were tested. The main data obtained were wall static pressure measurements, and the presence of combustion was determined based on the pressure rises obtained. Supersonic and dual-mode combustion were achieved with hydrogen and ethylene fuel, whereas very limited heat release was obtained with the methane. Global operability limits were determined to be 0.07 < ϕ < 0.31 for hydrogen, and 0.14 < ϕ < 0.48 for ethylene. The hydrogen fuel data for the aeroramp/torch system was compared to data from a physical 10° unswept compression ramp injector and similar performance was found with the two arrangements. With hydrogen and ethylene as fuels and the aeroramp/plasma-torch system, the effect of varying the air total temperature was investigated. Supersonic combustion was achieved with temperatures as low as 530K and 680K for the two fuels, respectively. These temperatures are facility/operational limits, not combustion limits. The pressure profiles were analyzed using the Ramjet Propulsion Analysis (RJPA) code. Results indicate that both supersonic and dual-mode ramjet combustion were achieved. Combustion efficiencies varied with ϕ from a high of about 75% to a low of about 45% at the highest ϕ. With a theoretical diffuser and nozzle assumed for the configuration and engine, thrust was computed for each fuel. Fuel specific impulse was on average 3000 and 1000 seconds for hydrogen and ethylene respectively, and air specific impulse varied from a low of about 9 sec to a high of about 24 sec (for both fuels) for the T o = 1000K test condition. The GASP RANS code was used to numerically simulate the injection and mixing process of the fuels. The results of this study were very useful in determining the suitability of the selected plasma torch locations. Further, this tool can be used to determine whether combustion is theoretically possible or not.

ISBN: 9780542338984Subjects--Topical Terms:

3433227
Aerospace materials.
Subjects--Index Terms:

Aeroramp

Scramjet operability range studies of an integrated aerodynamic-ramp-injector/plasma-torch igniter with hydrogen and hydrocarbon fuels.
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100 1 $a Bonanos, Aristides M. $3 3556262
245 1 0 $a Scramjet operability range studies of an integrated aerodynamic-ramp-injector/plasma-torch igniter with hydrogen and hydrocarbon fuels.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2005
300 $a 116 p.
500 $a Source: Dissertations Abstracts International, Volume: 67-08, Section: B.
500 $a Publisher info.: Dissertation/Thesis.
500 $a Advisor: Schetz, Joseph A.
502 $a Thesis (Ph.D.)--Virginia Polytechnic Institute and State University, 2005.
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 An integrated aerodynamic-ramp-injector/plasma-torch-igniter of original design was tested in a M∞ = 2, unvitiated, heated flow facility arranged as a diverging duct scramjet combustor. The facility operated at a total temperature of 1000 K and total pressure of 330 kPa. Hydrogen (H 2), ethylene (C2H4) and methane (CH4) were used as fuels, and a wide range of global equivalence ratios were tested. The main data obtained were wall static pressure measurements, and the presence of combustion was determined based on the pressure rises obtained. Supersonic and dual-mode combustion were achieved with hydrogen and ethylene fuel, whereas very limited heat release was obtained with the methane. Global operability limits were determined to be 0.07 < ϕ < 0.31 for hydrogen, and 0.14 < ϕ < 0.48 for ethylene. The hydrogen fuel data for the aeroramp/torch system was compared to data from a physical 10° unswept compression ramp injector and similar performance was found with the two arrangements. With hydrogen and ethylene as fuels and the aeroramp/plasma-torch system, the effect of varying the air total temperature was investigated. Supersonic combustion was achieved with temperatures as low as 530K and 680K for the two fuels, respectively. These temperatures are facility/operational limits, not combustion limits. The pressure profiles were analyzed using the Ramjet Propulsion Analysis (RJPA) code. Results indicate that both supersonic and dual-mode ramjet combustion were achieved. Combustion efficiencies varied with ϕ from a high of about 75% to a low of about 45% at the highest ϕ. With a theoretical diffuser and nozzle assumed for the configuration and engine, thrust was computed for each fuel. Fuel specific impulse was on average 3000 and 1000 seconds for hydrogen and ethylene respectively, and air specific impulse varied from a low of about 9 sec to a high of about 24 sec (for both fuels) for the T o = 1000K test condition. The GASP RANS code was used to numerically simulate the injection and mixing process of the fuels. The results of this study were very useful in determining the suitability of the selected plasma torch locations. Further, this tool can be used to determine whether combustion is theoretically possible or not.
590 $a School code: 0247.
650 4 $a Aerospace materials. $3 3433227
653 $a Aeroramp
653 $a Hydrocarbon
653 $a Hydrogen
653 $a Plasma torch
653 $a Scramjet
690 $a 0538
710 2 $a Virginia Polytechnic Institute and State University. $3 1017496
773 0 $t Dissertations Abstracts International $g 67-08B.
790 $a 0247
791 $a Ph.D.
792 $a 2005
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=3191731