Transverse Instability Studies in a Subscale Chamber

Pomeroy, Brian; Anderson, William E.

doi:10.2514/1.b35763

Cited by 31 publications

(8 citation statements)

References 19 publications

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“…The total reactant mass flow rate ( _ m) is 0.89 kg/s and is distributed equally between the injectors. The resulting Mach number in the injectors is 0.24 with a Reynolds number of 4 Â 10 5 . This corresponds to a jet velocity of 108 m/s at the exit of the injectors, which is within the range of values used in similar jet-stabilized combustion experiments.…”

Section: Combustor Designmentioning

confidence: 99%

“…1 These additional modes introduce multidimensional acoustic effects that generally occur at higher frequencies than those caused by longitudinal modes in gas turbine combustors. While highfrequency (HF) dynamics have been widely studied in rocket engines, [2][3][4][5][6] research on transverse instabilities and the mechanisms that cause them in gas turbine applications is relatively recent. 7 Multiple studies have been conducted to investigate the response of a flame and flow-field subjected to transverse acoustic waves.…”

Section: Introductionmentioning

confidence: 99%

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Injector-coupled transverse instabilities in a multi-element premixed combustor

Philo

Gejji

Slabaugh

2020

International Journal of Spray and Combustion Dynamics

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Combustion instabilities in a high-pressure, multi-element combustor are studied in order to understand the relationship between the chamber and injector dynamics. A linear array of seven injectors supplies premixed natural gas and air into a rectangular combustion chamber designed to promote high-frequency, transverse thermoacoustic instabilities. The effect of equivalence ratio on the combustion dynamics was investigated for two injector lengths, 62.5 and 125 mm. For all operating conditions, the 125 mm injectors promote high-amplitude instabilities of the fundamental transverse (1T) mode, which has a frequency of 1750–1850 Hz. Reducing the injector length significantly lowers the instability amplitudes for all operating conditions and, for lower equivalence ratio cases, excites an additional mode near 1550 Hz. The delineating feature controlling the growth of the instabilities in each injector configuration is the coupling with axial pressure fluctuations in the injectors that occur in response to the transverse modes in the chamber.

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Section: Combustor Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Injector-coupled transverse instabilities in a multi-element premixed combustor

Philo

Gejji

Slabaugh

2020

International Journal of Spray and Combustion Dynamics

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“…Fiber optics and sapphire lenses are used in both of these test articles to measure CH and OH emissions. A viewing window is incorporated into the transverse instability combustor facility, although this facility is limited to pressures of 1.4 MPa [15].…”

Section: G1mentioning

confidence: 99%

Optical Diagnostics in a High-Pressure Combustor with Gaseous Oxygen and Kerosene

Balance

Bibik

Cook

et al. 2019

Journal of Propulsion and Power

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“…Hot fire tests were conducted to study combustion instability in the chamber [3][4][5][6]. But the quantity of tests is needed due to the notoriously probability and uncertainty of combustion instability.…”

Section: Introductionmentioning

confidence: 99%

Numerical Analysis of Self-Excited Combustion Instabilities in a Small MMH/NTO Liquid Rocket Engine

Qin

Zhang

2020

International Journal of Aerospace Engineering

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Combustion instabilities in a small MMH/NTO liquid rocket engine used for satellite attitude and course control are numerically investigated. A three-dimensional Navier-Stokes code is developed to simulate two-phase spray combustion for cases with five different droplet Sauter Mean Diameters. As the droplet size increases from 30 microns to 80 microns, pressure oscillations are stronger with larger amplitudes. But an increase of the droplet size in the range of 80 microns to 140 microns indicates a reduction in the amplitudes of pressure oscillations. This trend is the same as the Hewitt criterion. The first tangential (1T) mode and the first longitudinal (1L) mode self-excited combustion instabilities are captured in the 60-micron and 80-micron cases. Abrupt spikes occur in the mass fraction of MMH and coincide with abrupt spikes in the mass fraction of NTO at the downstream regions just adjacent to the impinging points. Thus, local combustible high-dense mixtures are formed, which result in quasiconstant volume combustion and abrupt pressure spikes. The propagation and reflection of pressure waves in the chamber stimulate the combustion instability. When the droplet size is too small or too large, it is difficult to form local high-dense premixtures and combustion is stable in the chamber.

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Transverse Instability Studies in a Subscale Chamber

Cited by 31 publications

References 19 publications

Injector-coupled transverse instabilities in a multi-element premixed combustor

Injector-coupled transverse instabilities in a multi-element premixed combustor

Optical Diagnostics in a High-Pressure Combustor with Gaseous Oxygen and Kerosene

Numerical Analysis of Self-Excited Combustion Instabilities in a Small MMH/NTO Liquid Rocket Engine

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