Computational Investigation of Acoustics and Instabilities in a Longitudinal-Mode Rocket Combustor

Smith, Randolph; Ellis, Maxwell; Xia, Guoping; Sankaran, Venkateswaran; Anderson, William E.; Merkle, Charles L.

doi:10.2514/1.28125

Cited by 76 publications

(37 citation statements)

References 9 publications

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“…These include gaseous propellants, acoustically closed inlets and a converging diverging nozzle. 3 The combustion chamber is made up of three sections that are each five inches in length. High frequency pressure measurements are made at 100 kHz along the length of the combustor.…”

Section: Experimental Designmentioning

confidence: 99%

“…The design of the combustor is given in detail in previous work performed by Yu et al 4 The oxidizer injector is made of partial concentric openings that choke the oxidizer flow to provide welldefined acoustic boundary conditions, a better representation of a one-dimensional experiment, and reduced inletinduced instabilities. 3 Gaseous methane is used in this experiment to eliminate the variables introduced by atomization and vaporization. Methane was chosen because it is a hydrocarbon that produces CH* and it has been shown to produce spontaneous combustion instabilities of moderate amplitudes.…”

Section: Experimental Designmentioning

confidence: 99%

See 1 more Smart Citation

Comparison Between Simulation and Measurement of Self-Excited Combustion Instability

Feldman¹,

Harvazinski²,

Merkle³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Combustion instability arises from the coupling between unsteady combustion and acoustic modes in a combustion chamber. A study comprising concurrent experiment and LES simulation of a single element rocket combustor was conducted. The goal was to evaluate the a priori predictive ability of the computational model with regards to self-excited combustion instability, and to use the detailed results from the simulation to interpret the mechanism of self-excitation. Pressure modes and chemiluminescence from CH* were measured at high sampling rates. Direct comparisons between the experimental and computational results were made on the basis of instability frequency, pressure mode shapes, and limit cycle amplitude. All indicated generally good agreement. The light emission representing heat release from the experiment was qualitatively similar to the simulation. The detailed results from the simulation provided much greater insight into the complex phenomena, and showed the likely mechanism that drove high amplitude instability was a periodic ignition in the recirculation zone just downstream of the dump plane. The ignition occurred nearly simultaneously with the arrival of a compression wave traveling from downstream.

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Section: Experimental Designmentioning

confidence: 99%

Section: Experimental Designmentioning

confidence: 99%

Comparison Between Simulation and Measurement of Self-Excited Combustion Instability

Feldman¹,

Harvazinski²,

Merkle³

et al. 2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

show abstract

“…However, due to the problem£s complexity, this is not at all straightforward, and ¦nding some means for accurately predicting the instability prior to a full-scale development is of great value. Simulations of rocket engine instabilities via computations are promising, but they are still very much in development [1].…”

Section: Introductionmentioning

confidence: 99%

“…Theoretically, combustion response can be determined experimentally or from high-¦delity simulations, and can be used in stability predictions [1]. High-speed quantitative measurements of chemical species would be ideal, but have not yet been applied to the unstable rocket environment.…”

Section: Introductionmentioning

confidence: 99%

Use of filtered combustion light and backlit high-speed images in combustion stability studies

Pomeroy

Wierman

Anderson

2013

Progress in Propulsion Physics

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“…또한 액체추진제가 분사되는 경우에는 분사면에서의 임피던스가 매우 큰 값을 갖게 된 다. 따라서 이 경우에는 아래와 같은 형태의 압 력 감응 시간지연 모델이 적용되어 왔다 [6,19,20]. 여기서, [7].…”

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Development of Helmholtz Solver for Thermo-Acoustic Instability within Combustion Devices

Kim¹,

Choi²,

Cha³

2010

Journal of the Korean Society for Aeronautical Space Science

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In order to effectively predict thermo-acoustic instability within real combustors of rocket engines and gas turbines, in the present study, the Helmholtz equation in conjunction with the time lag hypothesis is discretized by the finite element method on three-dimensional hybrid unstructured mesh. Numerical nonlinearity caused by the combustion response term is linearized by an iterative method, and the large-scale eigenvalue problem is solved by the Arnoldi method available in the ARPACK. As a consequence, the final solution of complex valued eigenfrequency and acoustic pressure field can be interpreted as resonant frequency, growth rate, and modal shape for acoustic modes of interest. The predictive capabilities of the present method have been validated against two academic problems with complex impedance boundary and premixed flame, as well as an ambient acoustic test for liquid rocket combustion chamber with/without baffle.

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Computational Investigation of Acoustics and Instabilities in a Longitudinal-Mode Rocket Combustor

Cited by 76 publications

References 9 publications

Comparison Between Simulation and Measurement of Self-Excited Combustion Instability

Comparison Between Simulation and Measurement of Self-Excited Combustion Instability

Use of filtered combustion light and backlit high-speed images in combustion stability studies

Development of Helmholtz Solver for Thermo-Acoustic Instability within Combustion Devices

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