Servo-Stabilization of Low-Frequency Oscillations in a Liquid Bipropellant Rocket Motor

Marble, Frank E.; Cox, Dale W.

doi:10.2514/8.4542

Cited by 47 publications

(14 citation statements)

References 2 publications

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“…Stabilization of the combustion conditions was achieved by modulating the propellant injection rate through a capacitor controlled by a servomechanism with pressure feedback. Similar approaches were used by Marble and Cox [375] and Lee et al [376] to control the low-frequency instabilities in bipropellant liquid rocket engines. No experimental results based on this ''servo-stabilization'' concept were published, however, primarily due to the limitations in instrumentation, such as lack of fast-response sensors and actuators, at that time.…”

Section: Laboratory-scale Experimentsmentioning

confidence: 89%

Dynamics and stability of lean-premixed swirl-stabilized combustion

Huang

Yang

2009

Progress in Energy and Combustion Science

1,123

459

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Section: Laboratory-scale Experimentsmentioning

confidence: 89%

Dynamics and stability of lean-premixed swirl-stabilized combustion

Huang

Yang

2009

Progress in Energy and Combustion Science

1,123

459

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“…Such phenomena are specifically damaging in devices with large power densities, a situation prevailing in high-pressure systems (gas turbines, aeroengines, liquid propellant rockets). Early work on instabilities in liquid rocket engines has emphasized the role of time lag and its sensitivity to operating parameters (Crocco 1951, Crocco & Cheng 1956, Harrje & Reardon 1972, Marble & Cox 1953, Tsien 1952. Recent issues in combustion dynamics are found in modern gas turbines, which rely on premixed combustion to reduce NO x emissions but are more sensitive to resonant coupling, leading to instability.…”

Section: Combustion Dynamics Backgroundmentioning

confidence: 97%

Dynamics of Swirling Flames

Candel

Durox²,

Schuller³

et al. 2014

Annu. Rev. Fluid Mech.

372

157

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In many continuous combustion processes, such as those found in aeroengines or gas turbines, the flame is stabilized by a swirling flow formed by aerodynamic swirlers. The dynamics of such swirling flames is of technical and fundamental interest. This article reviews progress in this field and begins with a discussion of the swirl number, a parameter that plays a central role in the definition of the flow structure and its response to incoming disturbances. Interaction between the swirler response and incoming acoustic perturbations generates a vorticity wave convected by the flow, which is accompanied by azimuthal velocity fluctuations. Axial and azimuthal velocities in turn define the flame response in terms of heat release rate fluctuations. The nonlinear response of swirling flames to incoming disturbances is conveniently represented with a flame describing function (FDF), in other words, with a family of transfer functions depending on frequency and incident axial velocity amplitudes. The FDF, however, does not reflect all possible nonlinear interactions in swirling flows. This aspect is illustrated with experimental data and some theoretical arguments in the last part of this article, which concerns the interaction of incident acoustic disturbances with the precessing vortex core, giving rise to nonlinear fluctuations at the frequency difference.

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“…To link to this article : DOI: 10 Any correspondence concerning this service should be sent to the repository administrator: staff-oatao@listes-diff.inp-toulouse.fr…”

Section: Open Archive Toulouse Archive Ouverte (Oatao)mentioning

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

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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.

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Servo-Stabilization of Low-Frequency Oscillations in a Liquid Bipropellant Rocket Motor

Cited by 47 publications

References 2 publications

Dynamics and stability of lean-premixed swirl-stabilized combustion

Dynamics and stability of lean-premixed swirl-stabilized combustion

Dynamics of Swirling Flames

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

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