A Numerical Analysis of Supersonic Intake Buzz in an Axisymmetric Ramjet Engine

Yeom, Hyo Won; Sung, Hong-Gye; Yang, Vigor

doi:10.5139/ijass.2015.16.2.165

Cited by 4 publications

(1 citation statement)

References 25 publications

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“…The pressure in the plenum chamber increased when the shock accelerated back toward the cowl lip. Similarly, Yeom et al [84] examined the effect of buzz on flame oscillation, at M ∞ = 2.1, using a ramjet engine model, extending from the leading edge of the inlet to the exhaust nozzle. The authors recorded pressure readings throughout the entire length of the model.…”

Section: Physics and Characterization Of Intake Buzzmentioning

confidence: 99%

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

Philippou,

Zachos,

MacManus

2024

Aerospace

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High-speed air intakes often exhibit intricate flow patterns, with a specific type of flow instability known as `buzz’, characterized by unsteady shock oscillations at the inlet. This paper presents a comprehensive review of prior research, focused on unraveling the mechanisms that trigger buzz and its implications for engine stability and performance. The literature survey delves into studies concerning complex-shaped diffusers and isolators, offering a thorough examination of flow aerodynamics in unstable environments. Furthermore, this paper provides an overview of contemporary techniques for mitigating flow instability through both active and passive flow control methods. These techniques encompass boundary layer bleeding, the application of vortex generators, and strategies involving mass injection and energy deposition. The study concludes by discussing future prospects in the domain of engine-intake aerodynamic compatibility. This work serves as a valuable resource for researchers and engineers striving to address and understand the complexities of high-speed air induction systems.

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Section: Physics and Characterization Of Intake Buzzmentioning

confidence: 99%

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

Philippou,

Zachos,

MacManus

2024

Aerospace

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Experimental investigations of combustion oscillation modes in a large-aspect-ratio dual-mode combustor equipped with multi-strut

Qiu,

Luan,

Feng

et al. 2023

Physics of Fluids

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The annular scramjet combustor is considered one of the best configurations for a wide-speed-range combined engine, owing to its superior thermal protection performance and optimal geometric compatibility with rockets and turbines. To investigate the effect of fuel injection methods on the flame oscillation characteristics in the annular combustor, a scaled-down experiment was conducted on a fan-shaped combustor with a high aspect ratio equipped with multiple struts, utilizing liquid kerosene as the fuel. A series of experiments were conducted at the combustor inlet conditions of Ma = 2.7, Pt = 1.68 MPa, and Tt = 1640 K. High-speed cameras and pressure measurements were used in the experiments, and the flame images were processed using proper orthogonal decomposition. The findings revealed that under single-strut and multi-strut injection conditions, the flame oscillated in two modes: shear layer oscillation and central flame oscillation. As the equivalent ratio of injection strut increased, the oscillation frequency increased from 25 to 284 Hz, and the oscillation mode transition caused by the adverse pressure gradient occurred. The flashback was closely related to the combustion mode, and the distinct flame propagation processes under supersonic and subsonic flow conditions resulted in different oscillation characteristics. The experiment demonstrated that the flashback issue could be mitigated by increasing the spacing between the fuel injection struts. The study in this paper will provide important references for future research on flame oscillation and propagation characteristics in high-aspect-ratio annular combustors.

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Numerical Investigation of a Model Scramjet Combustor Using DDES

Shin

Sung

2017

International Journal of Turbo &Amp; Jet-Engines

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Non-reactive flows moving through a model scramjet were investigated using a delayed detached eddy simulation (DDES), which is a hybrid scheme combining Reynolds averaged Navier-Stokes scheme and a large eddy simulation. The three dimensional Navier-Stokes equations were solved numerically on a structural grid using finite volume methods. An in-house was developed. This code used a monotonic upstream-centered scheme for conservation laws (MUSCL) with an advection upstream splitting method by pressure weight function (AUSMPW+) for space. In addition, a 4th order Runge-Kutta scheme was used with preconditioning for time integration. The geometries and boundary conditions of a scramjet combustor operated by DLR, a German aerospace center, were considered. The profiles of the lower wall pressure and axial velocity obtained from a time-averaged solution were compared with experimental results. Also, the mixing efficiency and total pressure recovery factor were provided in order to inspect the performance of the combustor.

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A Numerical Analysis of Supersonic Intake Buzz in an Axisymmetric Ramjet Engine

Cited by 4 publications

References 25 publications

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

Aerodynamic Instabilities in High-Speed Air Intakes and Their Role in Propulsion System Integration

Experimental investigations of combustion oscillation modes in a large-aspect-ratio dual-mode combustor equipped with multi-strut

Numerical Investigation of a Model Scramjet Combustor Using DDES

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