Numerical Analysis and Optimization of Bleed Systems for External Supersonic Compression Inlets

Date

2025-01-01

Author

Özcan, Muhammed Enes
Sezer Uzol, Nilay

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A two-stage numerical study is conducted in order to enhance the functionality of the bleed system of a single-ramp, external-compression inlet. Initially, three-dimensional RANS simulations of eight representative perforated plates are utilized to calibrate a porous-jump model. This approach results in a cost reduction of the subsequent design survey by an order of magnitude, while maintaining pressure-loss accuracy within ±2%. A 53 full-factorial design (hole diameter, length-to-diameter ratio L/D, and porosity) comprising 125 geometries is then analyzed for the entry plate with the response-surface methodology, Shannon-entropy weighting, and multi-objective desirability optimization. The analysis of the variance demonstrates that porosity and L/D account for in excess of 95% of the sum of squares of the mass-flow ratio, drag coefficient and discharge coefficient. Conversely, the diameter is found to be statistically insignificant over the tested range. The optimization returns a compact entry-plate with the optimum L/D of 1.0 and the porosity of 0.20. Repeating the procedure for the exit plate, following the elimination of the weakly sensitive discharge coefficient, the optimum L/D of 0.25 and the porosity of 0.47 are obtained. These two optimized plates result in the enhancement of total-pressure recovery by 2.2–2.3% at the baseline buzz-onset points (MEF = 0.46 for M∞ = 1.6 and MEF = 0.48 for M∞ = 1.8–1.9), without any change in the captured mass flow rate. Furthermore, the aerodynamic buzz is delayed to the engine-face Mach numbers, 25–30% lower than the solid-wall configuration. The 19° bleed door results in the preservation of the recovery gain, concurrently delivering a further 1% increase and extending the stable operating envelope. The optimization of the porous plates with active bleed control provides a robust and Mach-independent means of enhancing the performance and operability of high-speed inlets.

Subject Keywords

Aerodynamic Instability, Boundary Layer Separation, Computational Fluid Dynamics, Cost Reduction, Design of Experiments, Discharge Coefficient, Entropy, Mass Flow Rate, Numerical Analysis, Terminal Normal Shock

URI

https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=105018468092&origin=inward
https://hdl.handle.net/11511/116503

Collections

Department of Aerospace Engineering, Conference / Seminar