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Computational Study of Partially Covered Hartmann Whistle in a Sonic-Underexpanded Jet

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Iranian Journal of Science and Technology, Transactions of Mechanical Engineering Aims and scope Submit manuscript

Abstract

The present study investigates the use of Hartmann whistle as an effective passive flow control device by partially covering the entire area between the jet exit and cavity inlet using a cylindrical shield, numerically. The passive flow control is accomplished by allowing the pulsating jet to exit through two small openings in the shield: (i) near the cavity inlet, (ii) away from the cavity inlet. The studies are performed for various S/Dj values of 1.43, 2.86 and 4.28, (where S is the stand-off distance and Dj is the jet diameter). The velocity vectors indicate the jet regurgitance showing inflow/outflow phases as well as flow diversion features near the cavity mouth. The Mach contours show shock-structures as well as the flow deceleration and re-acceleration zones. It shows that the resonant oscillations are primarily driven by jet regurgitance at smaller stand-off distances but at higher stand-off distances they are mainly driven by fluid column oscillations in the shock cells, shield, as well as in the cavity regions. It also shows that the stand-off distance is a key parameter that controls the strength of shock as well as regurgitant/fluid column, oscillations. An empirical formula developed using dimensional analysis reveals that the resonance frequency of the partially covered Hartmann whistles can be obtained using the classical Helmholtz resonator analogy with the stagnation sound speed, size of the flow control openings, shield height, stand-off distance and cavity length as parameters. Thus, this paper adequately illustrates the effect of stand-off distance as well as flow control openings in modifying the shock as well as regurgitant/fluid column, oscillations in a partially covered Hartmann whistle for attaining the effective flow control .

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Abbreviations

c o :

Stagnation speed of sound (m/s)

D c :

Cavity diameter (m)

D fej :

Fully expanded jet diameter (m)

D j :

Jet exit diameter (m)

d :

Diameter of the control openings (m)

H :

Radius of the cylindrical shield measured from the jet axis (m)

L :

Cavity length (m)

L shock :

Length of shock cell (m)

M e :

Mach number at the nozzle exit

P a :

Ambient pressure (bar)

P o :

Stagnation pressure (bar)

R :

Nozzle pressure ratio, (Po/Pa)

S :

Stand-off distance (m)

v j :

Jet velocity at nozzle exit (m/s)

ρ o :

Stagnation density (kg/m3)

References

  • Arnab S, Narayanan S, Jha SK, Narayan A (2017) Numerical simulation of a sonic-underexpanded jet impinging on a partially covered cylindrical Hartmann whistle, simulation. Trans Soc Model Simul Int. https://doi.org/10.1177/00375497177

    Article  Google Scholar 

  • Brocher E, Maresca C, Bournay MH (1970) Fluid dynamics of the resonance tube. J Fluid Mech 43(2):369–384

    Article  Google Scholar 

  • Brun E, Boucher RMG (1975) Research on the acoustic air-jet generator: a new development. J Acoust Soc Am 29(5):573–583

    Article  Google Scholar 

  • Chang SM, Lee S (2001) On the jet regurgitant mode of a resonant tube. J Sound Vib 246(4):567–581

    Article  Google Scholar 

  • Chang KS, Kim KH, Iwamoto J (1996) A study on the Hartmann Sprenger tube flow driven by a sonic jet. Int J Turbo Jet Engines 13:173–182

    Article  Google Scholar 

  • Gravitt JC (1959) Frequency response of an acoustic air-jet generator. J Acoust Soc Am 31(11):1516–1518

    Article  Google Scholar 

  • Gregory JW, Sullivan JP (2003) Characterization of Hartmann tube flow with porous pressure- sensitive paint. In: 33rd AIAA fluid dynamics conference and exhibit, June 23–26, Orlando, FL

  • Iwamoto J (1990) Experimental study of flow oscillation in a rectangular jet driven tube. Trans ASME J Fluids Eng 112(1):23–27

    Article  Google Scholar 

  • Kastner J, Samimy M (2002) Development and characterization of Hartmann tube fluidic actuators for high-speed flow control. Am Inst Aeronaut Astronaut J 40(10):1926–1934

    Article  Google Scholar 

  • McAlevy RF III, Pavlak A (1970) Tapered resonance tubes: some experiments. J Am Inst Aeronaut Astronaut 8(3):571–572

    Article  Google Scholar 

  • Michael E, Narayanan S, Abdul Jaleel H (2015) Numerical simulation of jet flow impinging on a shielded Hartmann whistle. Int J Aeronaut Sp Sci 16(2):123–136

    Article  Google Scholar 

  • Murugappan S, Gutmark E (2005) Parametric study of the Hartmann sprenger tube. Exp Fluids 38(6):813–823

    Article  Google Scholar 

  • Narayanan S, Bhave P, Srinivasan K, Ramamurthi K, Sundararajan T (2009) Spectra and directivity of a Hartmann whistle. J Sound Vib 321:875–892

    Article  Google Scholar 

  • Raman G, Srinivasan K (2009) The powered resonance tube: from Hartmann’s discovery to current active flow control applications. Prog Aerosp Sci 45:97–123

    Article  Google Scholar 

  • Ruan C, Xing F, Huang Y, Yu X, Zhang J, Yao Y (2017) The influence of acoustic field induced by HRT on oscillation behavior of a single droplet. Energies 10(1):48

    Article  Google Scholar 

  • Sobieraj GB, Szumowsky AP (1991) Experimental investigations of an underexpanded jet from a convergent nozzle impinging on a cavity. J Sound Vib 149(3):375–396

    Article  Google Scholar 

  • Spalart PR, Allmaras SR (1992) A one-equation turbulence model for aerodynamic flows. In: American Institute of Aeronautics and Astronautics AIAA-92-0439

  • Sreejith GJ, Narayanan S, Jothi TJS, Srinivasan K (2008) Studies on conical and cylindrical resonators. Appl Acoust 69(12):1161–1175

    Article  Google Scholar 

  • Tam CKW (1995) Jet noise generated by large-scale coherent motion. In: Hubbard HH (ed) Aeroacoustics of flight vehicles. Theory and practice, vol 1. Acoustical Society of America, Melville, p 1095

    Google Scholar 

  • Tam CKW, Tanna HK (1982) Shock associated noise of supersonic jets from convergent-divergent nozzles. J Sound Vib 81:337–358

    Article  Google Scholar 

Download references

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Authors and Affiliations

  1. Department of Mechanical Engineering, Indian Institute of Technology (Indian School of Mines), Dhanbad, 826004, India

    S. Narayanan, A. Samanta, Ashish Narayan & Shailesh Kumar Jha

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  1. S. Narayanan
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  2. A. Samanta
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  3. Ashish Narayan
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  4. Shailesh Kumar Jha
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Correspondence to S. Narayanan.

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Narayanan, S., Samanta, A., Narayan, A. et al. Computational Study of Partially Covered Hartmann Whistle in a Sonic-Underexpanded Jet. Iran J Sci Technol Trans Mech Eng 43, 639–661 (2019). https://doi.org/10.1007/s40997-018-0232-3

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  • DOI: https://doi.org/10.1007/s40997-018-0232-3

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