Thermal–Combustion Coupled Instability in Hybrid Rockets with Fuel Blowing

Lee, Jung-Pyo; Moon, Heejang; Kim, Jinkon

doi:10.2514/1.b38888

Cited by 2 publications

(2 citation statements)

References 15 publications

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“…This leads to a reduced heat transfer and subsequently reduced fuel gasification and fuel mass flow. In the following, this mass flow blocks a certain part of the heat transferred to the surface [4]. The respective low regression rate of HRM is a widely investigated disadvantage.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study on Post-Combustion Chamber Impact on Hybrid Rocket Performance

Dabanović,

Martin,

May

et al. 2024

Preprint

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In chemical propulsion, propellant masses are generally the largest part of the overall weight. Hence, combustion efficiency is a key aspect of the system’s performance and small improvements within the combustion process can result in significant changes in project costs or mission longevity. To analyze detailed chemical and physical processes, direct measurements are cost-intensive and limited to lab–scale devices. Numerical investigations have therefore become a widely used tool to simulate the inner flow and combustion of propulsion systems. In hybrid rocket engines, post–combustion chambers are used to improve the mixing and combustion process. Nevertheless, these components imply additional structural mass and engine length. This study analyzes the influence of different post-combustion chamber lengths on the combustion efficiency. The simulations were performed in two–dimensional, axisymmetric domains with fuel mass flow and detailed combustion modeling. The efficiency is shown to increase linearly with increasing post–chamber length. However, it is significantly influenced by turbulator components. With these results, the qualitative influence of post– combustion chambers is analyzed, enabling optimization of engine design while ensuring sufficient combustion efficiency.

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Section: Introductionmentioning

confidence: 99%

Numerical Study on Post-Combustion Chamber Impact on Hybrid Rocket Performance

Dabanović,

Martin,

May

et al. 2024

Preprint

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“…As a result of these phenomena, convective heat transfer and the rate of enthalpy exchange are significantly reduced [13]. In addition, at axial positions approaching the nozzle, the combustion zone is further removed from the combustion surface, representing the so-called blowing effect [14]. This effect can cause non-uniform fuel regression in the axial direction [15,16].…”

Section: Introductionmentioning

confidence: 99%

Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets

Wang,

Lin,

Wang

et al. 2023

Aerospace

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The combustion characteristics of a swirl-radial-injection composite fuel grain were experimentally and numerically investigated. This composite grain permits swirl-radial oxidizer injection based on three hollow helical blades, each having a constant hollow space allowing uniform oxidizer injection into the main chamber along the axial direction. The oxidizer enters from channel inlets located along a hollow outer wall. This wall, together with the three blades, is fabricated as one piece from acrylonitrile-butadiene-styrene using three-dimensional printing. Paraffin-based fuel is embedded in the spaces between adjacent blades. Firing tests were conducted with gaseous oxygen as the oxidizer, using oxidizer mass flow rates ranging from 7.45 to 30.68 g/s. Paraffin-based fuel grains using conventional fore-end injection were used for comparison. Regression rate boundaries were determined taking into account the erosion of the oxidizer channels. The data show that the regression rate was significantly increased even at the lower limit. Images of the combustion chamber flame and of the exhaust plume were also acquired. The flame was found to be concentrated in the main chamber and a smoky plume was observed, consistent with the high regression rate. A three-dimensional simulation was employed. The present design was found to improve fuel/oxidizer mixing and combustion efficiency compared with a fuel grain using fore-end injection. Both the experimental results and numerical simulations confirmed the potential of this swirl-radial-injection fuel grain.

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Thermal–Combustion Coupled Instability in Hybrid Rockets with Fuel Blowing

Cited by 2 publications

References 15 publications

Numerical Study on Post-Combustion Chamber Impact on Hybrid Rocket Performance

Numerical Study on Post-Combustion Chamber Impact on Hybrid Rocket Performance

Combustion Characteristics of a Swirl-Radial-Injection Composite Fuel Grain with Applications in Hybrid Rockets

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