Stability rating tests for the length-optimization of baffles in a liquid propellant combustion chamber using a pulse gun

Kim, Hong-jip; Seo, Seonghyeon; Lee, Kwang Jin; Han, Yeoung Min; Lee, Soo Yong; Young-Sung, Ko

doi:10.1016/j.ast.2007.06.003

Cited by 14 publications

(5 citation statements)

References 11 publications

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“…Slow failures or incipient faults, such as wearing of gears and small amount leakage of the propellant, can result in the deterioration of engine performance, but urgent (abrupt) failures, for example, leakage of fuel into the oxidizer pump, may lead to an engine explosion (Wu, 2005). Combustion instability, which is often induced by the interaction of the combustion zone and the acoustic field in a combustion chamber, can cause the deterioration of combustion performance and severe physical damage to the rocket combustor hardware, consequently resulting in a mission failure (Flandro et al, 2004;Kim et al, 2008). Failures in liquid rocket engine pressure vessels have many causes.…”

Section: Liquid Rocket Enginesmentioning

confidence: 99%

A review of flaws and damage in space launch vehicles: Motors and engines

Dhital

Lee

Farrar

et al. 2013

Journal of Intelligent Material Systems and Structures

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Rocket engines are complex systems which usually operate under extreme physical conditions such as very high temperature and pressure, strong erosion, and high-density energy release. Mechanical and chemical complexity, long service lives, aging materials, and designs with small margins of safety are typical for space launch vehicle components including the engine. Furthermore, these components can be exposed to various flaws and damage during the manufacturing, assembly, or ground handling phase. In regard to the engine, its performance characteristics can be significantly affected by the degradation resulting from such flaws and damages, which, in turn, might lead to failure of the entire space mission. Any manufacturing/operational damage needs to be detected at the earliest stage possible, so that the required preventive measures can be implemented, and component readiness and reliability must be checked either during manufacturing or during field inspections. This review study lists such possible flaws/damages on rocket engine components. This information could be beneficial for determining and developing the efficient techniques for reliable nondestructive evaluation and structural health monitoring.

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Section: Liquid Rocket Enginesmentioning

confidence: 99%

A review of flaws and damage in space launch vehicles: Motors and engines

Dhital

Lee

Farrar

et al. 2013

Journal of Intelligent Material Systems and Structures

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“…p(x, t), and q(x, t) are the local pressure and heat release rate, respectively. Over the past 2 decades, many investigations have been conducted, both experimentally (Kim et al, 2008;Ruan et al, 2020;Liu et al, 2021a) and theoretically (Culick, 1970;Coates and Horton, 1974;Bhatia and Sirignano, 1991;Sattelmayer, 2003). Typically, the longitudinal combustion instability has mostly been examined systematically at Purdue University (Smith et al, 2006(Smith et al, , 2010bYu, 2009;Wierman et al, 2012).…”

Section: Introductionmentioning

confidence: 99%

Three-Dimensional Numerical Analysis of Longitudinal Thermoacoustic Instability in a Single-Element Rocket Combustor

Guo

Ren

et al. 2022

Front. Energy Res.

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This study numerically investigated the thermoacoustic combustion instability characteristics of a scaled rocket combustor based on a hybrid of the Reynolds-averaged Navier–Stokes and large–eddy simulation method. The turbulence–combustion interactions were treated using flamelet generated manifold approach. An unstable case was simulated with detailed reaction mechanisms (GRI-Mech 3.0). The obtained results agree well with experiment data from Purdue University, in terms of pressure oscillations frequency and power spectral density spectrum. The combustion instability mode was identified to be coupled with the first longitudinal acoustic mode of the combustion chamber by dynamic model decomposition method. According to Rayleigh index analysis, the unstable driving source was found to be located near the combustor step, which was further confirmed by time-averaged flow fields. Detailed three-dimensional vortex ring shedding evolutions at the combustor step were tracked with fine time resolution. Results indicate that the combustion instability arises from periodic vortex ring shedding at the combustor step and interacting with the chamber wall. The unburnt reactants were rolled up by the shedding vortex ring, which would not break up until impact with the chamber wall. Therefore, the mixing performance was significantly enhanced, leading to sudden heat release. Consequently, the thermal energy is added to the acoustic field, and the first longitudinal mode is thus reinforced, giving rise to large amplitude axial velocity oscillations which prompt the generation of the new vortex ring. The results of the present investigation will support the design and development of high-performance rocket engines.

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“…Pressure oscillations have been observed in various combustion-driven systems, for example, in diesel engines, liquid propellant rockets, solid-propellant rockets and guns [2][3][4][5]. The pressure of a liquid propellant gun is 10 or even 100 times greater than that of a liquid propellant rocket, and the pressure oscillations may go up to several hundred of megapascals.…”

Section: Introductionmentioning

confidence: 99%

Study on Time‐frequency Characteristics of Pressure Oscillations in a Bulk‐loaded Liquid Gun

Mang

Zhang

2018

Propellants Explo Pyrotec

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The pressure oscillation in the bulk-load liquid gun is a kind of combustion instability and has adverse effects on the interior ballistic cycle. With different liquid propellants and different combustion chamber geometries, the combustion and propulsion experiments were conducted on a small calibre gun, and the behaviors of pressure oscillation were investigated. By the wavelet transform, the pressure oscillations were precisely extracted from the measured pressure-time curves. The oscillation characteristics were analyzed and compared in both the time domain and the frequency domain. Furthermore, a simplified acoustic resonance model considering the combustion-gas cavity expansion in liquid propellant was developed to estimate the range of the resonant frequency, and the relations between pressure oscillation and acoustic resonance were discussed. The experiments showed that the stepped-wall combustion chamber geometry was beneficial to reduce the pressure oscillation. The consistency of frequency range of the low-frequency oscillation between calculations and experiments suggested that axial acoustic resonance played a key role in producing the pressure oscillation, and the characteristics of the high-frequency oscillation were mainly affected by the combustion of liquid propellant droplets.

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Stability rating tests for the length-optimization of baffles in a liquid propellant combustion chamber using a pulse gun

Cited by 14 publications

References 11 publications

A review of flaws and damage in space launch vehicles: Motors and engines

A review of flaws and damage in space launch vehicles: Motors and engines

Three-Dimensional Numerical Analysis of Longitudinal Thermoacoustic Instability in a Single-Element Rocket Combustor

Study on Time‐frequency Characteristics of Pressure Oscillations in a Bulk‐loaded Liquid Gun

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