Effect of Centrifugal Force on Turbulent Premixed Flames

Briones, Alejandro M.; Sekar, Balu; Erdmann, Timothy J.

doi:10.1115/1.4028057

Cited by 29 publications

(2 citation statements)

References 10 publications

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“…When the swirl inlet is designed, the inlet directs fresh air to the main combustion area. It is necessary to control the g -loading value after the swirl enters the combustion chamber between 500 and 3500 g 0 to avoid flame quenching due to flame instability caused by a g -loading value of more than 3500 g 0 , , while simultaneously increasing the g -loading value to the maximum possible extent to increase the flame propagation rate. When the inlet area is certain, the higher the inlet flow rate, the higher the inlet velocity and the larger the g -loading value.…”

Section: Resultsmentioning

confidence: 99%

“…The superior combustion performance of high- g technology has motivated many researchers to conduct experiments to verify this phenomenon, − and numerous studies have been conducted to obtain a more detailed flame mechanism through simulations. − Recently, researchers have pointed out that the high- g combustion mechanism is more complex and may be related to the Rayleigh–Taylor instability. − Briones et al reproduced Lewis’s experiments using a two-dimensional computational domain to simulate a rotating combustion tube and found that higher values of g -loading were not better, and at larger values of g -loading, the flame front broke up and disrupted its own mixing with the fuel, which led to localized quenching and slowed down flame propagation. Briones proposed that Rayleigh–Taylor instability affects the localized flow rate of the flame and thus the flame propagation rate.…”

Section: Introductionmentioning

confidence: 99%

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Gear-Shaped High-g Combustion Chamber for Micro Turbojet Engine Applications

Huang,

Chen,

long

et al. 2024

ACS Omega

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Enhancing combustion efficiency and optimizing the thrust-toweight ratio are critical technical challenges encountered in the development, application, and growth of micro turbojet engines. The high-centrifugal (high-g) combustion chamber, as an innovative combustion chamber system, has the capability to replace the primary combustion chamber of the traditional turbojet engine, reducing the length of the combustion chamber while maintaining engine performance. Previous studies on the structure of the high-g combustor (HGC) have shown problems such as uneven temperature distribution of the turbojet rotor. To improve the feasibility of HGC integration into micro turbojet engines, this study conducts relevant experiments on a 120 N thrust engine. Subsequently, the results of these experiments were used to analyze the structural design of HGC through a simulation approach. Including six main configurations, the first four structural designs focused on establishing a suitable highly centrifugal environment to stabilize and improve the combustion performance, which was successfully achieved by designing the outer ring gearshaped inlet with four different angles. Subsequent structural designs were based around improving the uniformity of the temperature distribution at the combustion chamber outlet. The final design of the HGC combustion efficiency is not much different from the original combustion chamber, and it can shorten the axial length of the combustion chamber by nearly 30%. The design of the air inlet holes and the baffle plate effectively improves the temperature uniformity at the outlet of the combustion chamber. Moreover, without changing the combustion chamber material, the corresponding engine weight can be reduced by about 10.7%, and the engine thrust-to-weight ratio can be improved by up to 12% with the same thrust, which provides design ideas for further lightweight applications.

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Section: Resultsmentioning

confidence: 99%