Analysis of shock oscillations of an external compression supersonic inlet through unsteady numerical simulations

Grenson, Pierre; Beneddine, Samir

doi:10.2514/6.2018-3011

Cited by 6 publications

(6 citation statements)

References 20 publications

(24 reference statements)

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“…More recently, Grenson and Beneddine [80] showed that pressure varies periodically across the duct, but the fluctuations are not in-phase between the fore and rear part of the duct during little buzz, as it would be expected for the fundamental duct acoustic mode (n = 0). While many studies show how the observed frequency of little buzz is closely related to the fundamental frequency of the acoustic mode, Grenson and Benedine [86] have observed little buzz frequency to be significantly lower.…”

Section: Physics and Characterization Of Intake Buzzmentioning

confidence: 96%

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: 96%

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

Philippou,

Zachos,

MacManus

2024

Aerospace

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“…A bypass system collects the excess flow, diffuses it to subsonic speeds and exhausts it radially to enable unobstructed optical access to a large part of the subsonic diffuser section of the intake (Figure 2). This allows nonintrusive optical measurements at the AIP without the potential difficulties associated with integrating optical instrumentation within the wind tunnel walls [14] [15] [16]. The radial bypass exhaust system is still under development.…”

Section: Intake Rig Overall Plant Architecturementioning

confidence: 99%

“…It is known that the detailed aerodynamics near the entry of a supersonic intake can strongly influence the performance of its subsonic diffuser [14]. This is particularly important near the stability limit of the intake which influenced the need of previously developed test facilities to aid the understanding of the interactions between unsteady cowl aerodynamics and the subsonic diffuser [15] [16].…”

Section: Working Section Design and Model Integrationmentioning

confidence: 99%

Design of a high-speed intake distortion simulator for propulsion integration research

Migliorini

Szymański

Zachos

et al. 2023

AIAA SCITECH 2023 Forum

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High levels of inlet flow distortion can be a critical aspect in supersonic air induction systems due to the complex spatial nature and notable temporal unsteadiness. This can affect the operability and performance of the propulsion system. Simulation of the intake shock system in a relatively less expensive, lower technology readiness level experimental facility can be an important element to mitigate a significant part of the risk that industrial and certification testing carries. The work described in this paper is part of a programme that aims to develop such a distortion simulation test rig where the capability of advanced nonintrusive measurement techniques would be applied in propulsion integration research. The paper describes the concept, preliminary design and sizing of the working section of the rig, the exhaust system design and the integration of the test model. A brief summary of the rig architecture is provided along with details of the high-pressure system that drives the supersonic flow. The work indicates that careful design of the working section is required to ensure sufficient operating range and representative aerodynamics of the test model. It is also shown that the working section wall interference on the test model is tightly linked with the type and size of the aircraft intake to be tested. Ways to mitigate this interference are herein explored. I.Nomenclature ACIntake capture area AH Working section cross-sectional area A0 Area of stream tube entering the inlet Amax Maximum inlet projected area, A* Nozzle throat area Cp Static pressure coefficient H Working section height Ht Intake throat height h Diverter height

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“…However, the present work is focused on the performances of a started inlet in off-design conditions and so the buzz phenomenon is not investigated here but only the average fields in the started inlet are required. In the literature it is possible to find some examples of large eddy simulations (LES) [37,38] and hybrid RANS-LES simulations [39,40]: these approaches can give a more detailed description of the turbulence phenomena that take place inside the inlet with respect to RANS models and so they can give a more accurate prediction of the inlet performance. However, they have mainly been adopted for studying the buzz in the subcritical regime and the starting transient of the inlet.…”

Section: Compressible Reynolds-averaged Navier-stokes (Rans) Equationsmentioning

confidence: 99%

Control of a Supersonic Inlet in Off-Design Conditions with Plasma Actuators and Bleed

Ferrero

2020

Aerospace

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Supersonic inlets are a key component of present and future air-breathing propulsion systems for high-speed flight. The inlet design is challenging because of several phenomena that must be taken under control: shock waves, boundary layer separation and unsteadiness. Furthermore, the intensity of these phenomena is strongly influenced by the working conditions and so active control systems can be particularly useful in off-design conditions. In this work, a mixed compression supersonic inlet with a double wedge ramp is considered. The flow field was numerically investigated at different values of Mach number. The simulations show that large separations appear at the higher Mach numbers on both the upper and lower walls of the duct. In order to improve the performances of the inlet two different control strategies were investigated: plasma actuators and bleed. Different locations of the plasma actuator are considered in order to also apply this technology to configurations with a diverter which prevents boundary layer ingestion. The potential of the proposed solutions is investigated in terms of total pressure recovery, flow distortion and power consumption.

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Analysis of shock oscillations of an external compression supersonic inlet through unsteady numerical simulations

Cited by 6 publications

References 20 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

Design of a high-speed intake distortion simulator for propulsion integration research

Control of a Supersonic Inlet in Off-Design Conditions with Plasma Actuators and Bleed

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