Date of Award
2025
Document Type
Thesis
Degree Name
Master of Science in Aerospace and Systems Engineering (MSASE)
Department
Mechanical and Aerospace Engineering
Committee Chair
John W. Bennewitz
Committee Member
Kader Frendi
Committee Member
David Lineberry
Research Advisor
John W. Bennewitz
Subject(s)
Rocket engines--Design and construction, Space vehicles--Propulsion systems, Rotating detonation rocket engine (RDRE)
Abstract
Rotating detonation rocket engines (RDREs) are propulsion devices that harness circumferentially traveling detonation waves, providing theoretical benefits compared to classical, deflagration-based combustors. Because of the integration challenges posed by typical annular (Center Body, CB) RDREs, a cylindrical (Center Bodiless, CBL) chamber geometry is attractive. To understand the corresponding trade-offs for small-scale devices, the performance and operational characteristics for a 25 mm with removable 15 mm center body are compared using gaseous methane and hydrogen with oxygen, operating at varying equivalence ratios and at a total mass flow rate of 0.076 kg/s and varying mass flow rates at an equivalence ratio of 1.25 and 1.0. The operability of the CB geometry is greater than the CBL configuration. Additionally, thrust and specific impulse performance are generally greater for the CB than for the CBL geometry. These results of this thesis have implications for downwards RDRE mass flow rate scaling.
Recommended Citation
Durkee, Kaito Jonathan, "Performance comparison of variable center body configurations for a 25 mm rotating detonation rocket engine" (2025). Theses. 757.
https://louis.uah.edu/uah-theses/757
