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Investigation of Pre-ignition Propel...

Roberts, Quentin.

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Investigation of Pre-ignition Propellant Mixing in Rotating Detonation Rocket Engine.

Record Type:	Electronic resources : Monograph/item
Title/Author:	Investigation of Pre-ignition Propellant Mixing in Rotating Detonation Rocket Engine./
Author:	Roberts, Quentin.
Published:	Ann Arbor : ProQuest Dissertations & Theses, : 2023,
Description:	75 p.
Notes:	Source: Masters Abstracts International, Volume: 85-01.
Contained By:	Masters Abstracts International85-01.
Subject:	Aerospace engineering. -
Online resource:	https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30316708
ISBN:	9798379909901

Investigation of Pre-ignition Propellant Mixing in Rotating Detonation Rocket Engine.
Roberts, Quentin.

Investigation of Pre-ignition Propellant Mixing in Rotating Detonation Rocket Engine. - Ann Arbor : ProQuest Dissertations & Theses, 2023 - 75 p.

Source: Masters Abstracts International, Volume: 85-01.

Thesis (M.S.)--University of Washington, 2023.

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

Pre-ignition propellant mixing was simulated using computational fluid dynamics in various rotating detonation rocket engine (RDRE) configurations. Two different RDREs were used for the simulations, a 25.4 mm diameter RDRE and a 10 mm diameter RDRE. The 25.4 mm diameter RDRE used multiple configurations, with different core plug sizes producing a 3 mm, 5 mm, and 7 mm wide annular combustion chamber, as well as a coreless cylindrical 25.4 mm diameter combustion chamber configuration. The 25.4 mm RDRE used methane and oxygen propellants. The 10 mm diameter RDRE was operated and simulated only in a coreless configuration, but with both methane and oxygen propellants, and hydrogen and oxygen propellants. Four cases for each configuration were simulated, three with similar total mass flow rates and equivalence ratios near stoichiometric, fuel rich, and fuel lean, and the fourth varying total mass flow rate. Mixing was simulated in ANSYS Fluent using a standard k-ω turbulence model, and a non-reacting species transport model. Simulation results were verified by comparing simulated wall pressure data and injector discharge coefficient data with experimental data. Average mixedness and mixed layer location versus distance from the injector face were compared across the simulated RDREs, propellant combinations, configurations and cases. Frames from high speed video of experimental hot fire tests were compared with simulations, comparing radial mixing trends with radial luminosity profiles.

ISBN: 9798379909901Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Computational fluid dynamics

Investigation of Pre-ignition Propellant Mixing in Rotating Detonation Rocket Engine.
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100 1 $a Roberts, Quentin. $3 3766933
245 1 0 $a Investigation of Pre-ignition Propellant Mixing in Rotating Detonation Rocket Engine.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2023
300 $a 75 p.
500 $a Source: Masters Abstracts International, Volume: 85-01.
500 $a Advisor: Knowlen, Carl.
502 $a Thesis (M.S.)--University of Washington, 2023.
506 $a This item must not be sold to any third party vendors.
520 $a Pre-ignition propellant mixing was simulated using computational fluid dynamics in various rotating detonation rocket engine (RDRE) configurations. Two different RDREs were used for the simulations, a 25.4 mm diameter RDRE and a 10 mm diameter RDRE. The 25.4 mm diameter RDRE used multiple configurations, with different core plug sizes producing a 3 mm, 5 mm, and 7 mm wide annular combustion chamber, as well as a coreless cylindrical 25.4 mm diameter combustion chamber configuration. The 25.4 mm RDRE used methane and oxygen propellants. The 10 mm diameter RDRE was operated and simulated only in a coreless configuration, but with both methane and oxygen propellants, and hydrogen and oxygen propellants. Four cases for each configuration were simulated, three with similar total mass flow rates and equivalence ratios near stoichiometric, fuel rich, and fuel lean, and the fourth varying total mass flow rate. Mixing was simulated in ANSYS Fluent using a standard k-ω turbulence model, and a non-reacting species transport model. Simulation results were verified by comparing simulated wall pressure data and injector discharge coefficient data with experimental data. Average mixedness and mixed layer location versus distance from the injector face were compared across the simulated RDREs, propellant combinations, configurations and cases. Frames from high speed video of experimental hot fire tests were compared with simulations, comparing radial mixing trends with radial luminosity profiles.
590 $a School code: 0250.
650 4 $a Aerospace engineering. $3 1002622
650 4 $a Fluid mechanics. $3 528155
653 $a Computational fluid dynamics
653 $a Injector mixing
653 $a Oxygen propellants
653 $a ANSYS Fluent
690 $a 0538
690 $a 0204
710 2 $a University of Washington. $b Aeronautics and Astronautics. $3 2093881
773 0 $t Masters Abstracts International $g 85-01.
790 $a 0250
791 $a M.S.
792 $a 2023
793 $a English
856 4 0 $u https://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=30316708