A Computational Study on the Effect of Angles of Attack on a Double-Cone Type Supersonic Inlet With Bleeding System

Ryu, Kyung Jin; Lim, Seol; Kim, Sang Dug; Song, Dong Joo

doi:10.1115/gt2010-23221

Cited by 3 publications

(2 citation statements)

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“…It was of interest to identify effects of a fixed geometry bleed on the intake performance at off-design conditions including different free stream Mach numbers and angles of attack in some investigations. 21,[57][58][59] According to these studies, even a fixed geometry bleed has beneficial effects on the intake performance at off-design conditions as seen from Figures 22 and 23. However, experimental studies of Soltani et al 21 showed that for M 1 ¼ 1.8, using the bleed at off-design condition may result in destructive effects for some special cases (Figure 24).…”

Section: Effectiveness Of the Bleed At Off-design Conditionsmentioning

confidence: 99%

Boundary layer suction for high-speed air intakes: A review

Sepahi-Younsi

Feshalami

Maadi

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The paper summarizes recent developments in boundary layer suction for high-speed air intakes. Bleed has been efficiently used in supersonic and hypersonic intakes for three primary reasons: to improve the performance of the intake, to reduce the starting Mach number of the intake, and to postpone the onset of buzz oscillations. A bleed system has many characteristics such as the bleed entrance and exit areas, bleed entrance slant angle and position, and bleed type (slot or porous and ram-scoop or flush). Each of these parameters has significant impacts on the intake performance and stability that have been reviewed in this study. In addition, the effectiveness of other flow control methods has been compared with the bleed method.

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Section: Effectiveness Of the Bleed At Off-design Conditionsmentioning

confidence: 99%

Boundary layer suction for high-speed air intakes: A review

Sepahi-Younsi

Feshalami

Maadi

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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show abstract

“…For example, large regions of laminar flow for an aircraft can be realized in flight using slotsuction laminar flow control, leading to a pronounced reduction in drag and a remarkable improvement in fuel efficiency [3]. For transonic wings and supersonic inlets, the overall performance is significantly affected by the presence of shock wave-boundary layer interactions (SWBLIs) and boundary layer bleed can be used to reduce the adverse effects of SWBLIs [4][5][6][7]. At wind tunnels, bleed slots can be employed to maintain a laminar boundary layer on the nozzle wall and avoid acoustic fluctuations generated by boundary layer turbulence, further replicating the low noise conditions of actual flight [8].…”

Section: Introductionmentioning

confidence: 99%

Aerothermal characteristics of bleed slot in hypersonic flows

Yue

et al. 2015

Sci. China Phys. Mech. Astron.

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Two types of flow configurations with bleed in two-dimensional hypersonic flows are numerically examined to investigate their aerodynamic thermal loads and related flow structures at choked conditions. One is a turbulent boundary layer flow without shock impingement where the effects of the slot angle are discussed, and the other is shock wave boundary layer interactions where the effects of slot angle and slot location relative to shock impingement point are surveyed. A key separation is induced by bleed barrier shock on the upstream slot wall, resulting in a localized maximum heat flux at the reattachment point. For slanted slots, the dominating flow patterns are not much affected by the change in slot angle, but vary dramatically with slot location relative to the shock impingement point. Different flow structures are found in the case of normal slot, such as a flow pattern similar to typical Laval nozzle flow, the largest separation bubble which is almost independent of the shock position. Its larger detached distance results in 20% lower stagnation heat flux on the downstream slot corner, but with much wider area suffering from severe thermal loads. In spite of the complexity of the flow patterns, it is clearly revealed that the heat flux generally rises with the slot location moving downstream, and an increase in slot angle from 20° to 40° reduces 50% the heat flux peak at the reattachment point in the slot passage. The results further indicate that the bleed does not raise the heat flux around the slot for all cases except for the area around the downstream slot corner. Among all bleed configurations, the slot angle of 40° located slightly upstream of the incident shock is regarded as the best.

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A Numerical Study on the Effect of Bleed System on Starting Ability and Flow Performance of Rampressor Inlet

Kang

Liu

Wang

et al. 2014

Journal of Engineering for Gas Turbines and Power

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A unique supersonic compressor rotor with high pressure ratio, termed the Rampressor, is presented by Ramgen Power Systems, Inc., (RPS). Based on the models of Rampressor inlet, the inlet flow field with bleed system is numerically studied. Validation of the employed computational fluid dynamics (CFD) scheme is provided through test cases. The effects of boundary layer bleed location and bleed amount on Rampressor rotor inlet start and flow performance are analyzed. The results indicate that the boundary layer bleed has a significant effect for start and flow performance of Rampressor inlet. Bound ary layer bleed technique has been applied to eliminate the emerging flow separation zone for enhancing Rampressor rotor inlet performance and enlarging its stable working range. The starting ability and flow performance of Rampressor inlet are efficiently improved by bleeding system, but the improvement effect is different for Rampressor inlet with different bleed location. Along the position of bleeding system moves forward, the range of Rampressor inlet normal work rotation speed is enlarged. The flow performance of Rampressor inlet improves obviously with the increment of bleed flow rate, and exit stability of Rampressor inlet enhances. And in the same back pressure work condition of Rampressor inlet, bleed system has been shown to be effective that exit stability of Rampressor inlet ameliorates, but the loss of compressed air from the bleed system has a negative effect on overall Rampressor inlet efficiency.

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A Computational Study on the Effect of Angles of Attack on a Double-Cone Type Supersonic Inlet With Bleeding System

Cited by 3 publications

References 0 publications

Boundary layer suction for high-speed air intakes: A review

Boundary layer suction for high-speed air intakes: A review

Aerothermal characteristics of bleed slot in hypersonic flows

A Numerical Study on the Effect of Bleed System on Starting Ability and Flow Performance of Rampressor Inlet

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