Contributions of atomization to F-1 engine combustion instabilities

Chao, Chien-Chi; Heister, S. D.

doi:10.1016/j.enganabound.2004.04.003

Cited by 8 publications

(4 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The process in turn produces heat release fluctuation. A number of studies [11,[295][296][297][298][299][300][301][302][303][304][305][306][307] dealing with the role of atomization and spray vaporization on combustion instability have been conducted on liquid-fueled propulsion systems.…”

Section: Oscillatory Liquid Fuel Atomization and Droplet Evaporationmentioning

confidence: 99%

Dynamics and stability of lean-premixed swirl-stabilized combustion

Huang

Yang

2009

Progress in Energy and Combustion Science

1,123

459

View full text Add to dashboard Cite

Section: Oscillatory Liquid Fuel Atomization and Droplet Evaporationmentioning

confidence: 99%

Dynamics and stability of lean-premixed swirl-stabilized combustion

Huang

Yang

2009

Progress in Energy and Combustion Science

1,123

459

View full text Add to dashboard Cite

“…Here, dn is the injector hole diameter and V is the injection velocity for the impinging jet injector. There have been a few proposed mechanisms, such as jet atomization frequency (Anderson et al [5]), flame straining/extinction (Kim and Williams [17]), and fuel jet aerodynamic excitation (Chao and Heister [18]) attempting to offer explanations of the trend seen in Hewitt correlation. Although none has been fully proven as an established fact and a combined effect of several mechanisms can be in play, the author's hypothesis is a new perspective to the list.…”

Section: Extent Of Dark-core Oscillationsmentioning

confidence: 99%

Physical Hypothesis for the Combustion Instability in Cryogenic Liquid Rocket Engines

Chehroudi¹

2010

Journal of Propulsion and Power

View full text Add to dashboard Cite

In this work, the author would like to portray a sketch of a fluid dynamical picture to describe the coupling nature/ strength between the chamber acoustics and the injectors. This new perspective is achieved through a physically intuitive argument combined with previously published test results for two popular injector designs, namely, coaxial and impinging jets. For the impinging jet injectors, it is shown that the dynamic behavior of the dark-core (or breakup) zone for each jet, their lengths and thicknesses, has a profound impact on injector sensitivity to disturbances in its surrounding. This information is used to offer a possible explanation for the trends seen on the Hewitt stability plot in impinging jet injectors. Nomenclature d j = jet diameter from a hole d n = hole diameter of the injector L C;Pth = average liquid core length P th = threshold chamber pressure P ch = chamber pressure l = liquid density g = gas density T ch = chamber temperature V = average liquid jet exit velocity = impinging jet included half-angle

show abstract

“…This is exemplified in a book edited by Yang and Anderson [3] , in the monograph written by Culick [12] and in many further investigations. In the recent period, many studies pursue the analytical modeling of the driving mechanisms as for example [13][14][15][16][17][18][19] while new model scale experiments and scaling methods are reported in [20][21][22][23][24][25][26][27][28][29][30][31] . These experiments have provided novel information on the interaction between the combustion region and acoustic modes with much attention focused on transverse modes which are only weakly damped in thrust chambers and are consequently the most dangerous (the detrimental effect of transverse modes was already well recognized during the early period [11,32] ).…”

Section: Introductionmentioning

confidence: 99%

Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

Urbano

Selle

Staffelbach

et al. 2016

Combustion and Flame

177

View full text Add to dashboard Cite

et al.. Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector Liquid Rocket Engine. Combustion and Flame, Elsevier, 2016, 169, pp. a b s t r a c tThis article explores the possibility of analyzing combustion instabilities in liquid rocket engines by making use of Large Eddy Simulations (LES). Calculations are carried out for a complete small-scale rocket engine, including the injection manifold thrust chamber and nozzle outlet. The engine comprises 42 coaxial injectors feeding the combustion chamber with gaseous hydrogen and liquid oxygen and it operates at supercritical pressures with a maximum thermal power of 80 MW. The objective of the study is to predict the occurrence of transverse high-frequency combustion instabilities by comparing two operating points featuring different levels of acoustic activity. The LES compares favorably with the experiment for the stable load point and exhibits a nonlinearly unstable transverse mode for the experimentally unstable operating condition. A detailed analysis of the instability retrieves the experimental data in terms of spectral features. It is also found that modifications of the flame structures and of the global combustion region configuration have similarities with those observed in recent model scale experiments. It is shown that the overall acoustic activity mainly results from the combination of one transverse and one radial mode of the chamber, which are also strongly coupled with the oxidizer injectors.

show abstract

Contributions of atomization to F-1 engine combustion instabilities

Cited by 8 publications

References 9 publications

Dynamics and stability of lean-premixed swirl-stabilized combustion

Dynamics and stability of lean-premixed swirl-stabilized combustion

Physical Hypothesis for the Combustion Instability in Cryogenic Liquid Rocket Engines

Exploration of combustion instability triggering using Large Eddy Simulation of a multiple injector liquid rocket engine

Contact Info

Product

Resources

About