Investigation of Flow Turning in a Natural Blockage

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Presentation transcript:

Investigation of Flow Turning in a Natural Blockage Thrust Reverser S. Hall, R.K. Cooper, E. Benard & S. Raghunathan School of Aeronautical Engineering, Queen’s University Belfast, N.Ireland

Thrust Reversers are used to :- Provide extra safety margin during landing and aborted take offs. Expedite ground manoeuvring at congested airports. Natural Blockage Cascade Fan Flow Reverser (CF34-8C, CRJ-700)

Model Geometry CF34-8C (Reverser Deployed) Simplified Model Geometry

Why Low-Speed Testing? Testing at full-scale engine conditions is costly and requires sophisticated test facilities and equipment. Computational Studies suggest that compressibility effects are not dominant. M=0.1 M=0.4

Experimental Model Experiment Features:- 50% scale duct. Test Section: 380mm by 89mm Max Inlet Vel: 13.3m/s

Computational Analysis Computational Model Features:- Unstructured mesh (46726 cells) Farfield boundaries: 20 model lengths upstream/vertically 10 model lengths downstream Entrainment flow on upstream wall Solution:- 2D, incompressible steady, 1st order Reynolds Averaged Navier-Stokes equations (RANS) RNG K- turbulence model.

Results for Surface Static Pressure Coefficient Duct Upper Surface Duct Lower Surface

Results for cascade post-exit pressure rake (NPR=1.0033) Velocity vectors at rake position Rake total pressure coefficient

Comparison of Experimental/CFD data (NPR=1.0033) Static Pressure Coefficient Bottom Wall Static Pressure Coefficient Upper Wall

Conclusion Experiment successfully models qualitative aspects of flow through the reverser despite low nozzle pressure ratios. 2D CFD results show that 3D effects and flow separation in reverser flow are significant. 3D model simulations recommended.