Acoustic igniter parametric study for liquid propellant rocket engine applications

Date

2024-9-05

Author

Taşcı, Metehan

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Acoustic/Resonant ignition is a promising concept for liquid propellant rocket engines. Acoustic igniters have three main advantages over other types of igniters. First, they allow multiple engine starts. Second, they heat the gas using gas dynamics only, so no external power source is required. Third, they do not have moving parts, which makes them reliable. However, the complexity of the gas dynamics heating makes the design process difficult. Due to this reason, various numerical and experimental studies are conducted in the literature analyzing the effects of different design parameters and operating conditions. In this study, the cold gas design and heating phenomenon of an acoustic igniter for kerosene-oxygen propellants are studied. A design based on available knowledge in the literature is prepared and tested with a numerical study which employed Siemens StarCCM+ software. The numerical study also provided a great insight for the flow and the heating phenomenon. Then, various models of igniters have been 3-D printed from Inconel 718 material besides the initial design to study the effect of the variation of design parameters on heating performance. The dominant frequency of the sound emitted by the tube and tube end temperature are the two main outputs of the igniters in the cold gas design phase. The outputs of the numerical and experimental studies are compared. The problems encountered due to the 3-D design of the igniters are mentioned, and their solutions are provided.

Subject Keywords

Acoustic igniter, Resonant igniter, Liquid propellant rocket engine, Gas dynamics heating

URI

https://hdl.handle.net/11511/111449

Collections

Graduate School of Natural and Applied Sciences, Thesis