Influence of nozzle exit geometrical parameters on supersonic jet decay
-
Prasanta Kumar Mohanta
Abstract
Experiments and simulations were carried on C-D nozzles with four different exit geometry aspect ratios to investigate the impact of supersonic decay characteristics. Rectangular and elliptical exit geometries were considered for the study with various aspect ratios. Numerical simulations and Schlieren image study were studied and found the agreeable logical physics of decay and spread characteristics. The supersonic core decay was found to be of different length for different exit geometry aspect ratio, though the throat to exit area ratio was kept constant to maintain the same exit Mach number. The impact of nozzle exit aspect ratio geometry was responsible to enhance the mixing of primary flow with ambient air, without requiring a secondary method to increase the mixing characteristics. The higher aspect ratio resulted in better mixing when compared to lower aspect ratio exit geometry, which led to reduction in supersonic core length. The behavior of core length reduction gives the identical signature for both under-expanded and over-expanded cases. The results revealed that higher aspect ratio of the exit geometry produced smaller supersonic core length. The aspect ratio of cross section in divergent section of the nozzle was maintained constant from throat to exit to reduce flow losses.
-
Author contribution: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
-
Research funding: None declared.
-
Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
References
1. Kaushik, M, Rathakrishnan, E. Tab aspect ratio effect on supersonic jet mixing. Int J Turbo Jet Engines 2015;32:265–73. https://doi.org/10.1515/tjj-2014-0032.Search in Google Scholar
2. Bajpai, A, Rathakrishnan, E. Tab geometry effect on supersonic elliptic jet control. Int J Turbo Jet Engines 2017;34:395–408. https://doi.org/10.1515/tjj-2016-0020.Search in Google Scholar
3. Ezhilmaran, G, Khandai, SC, Pavithrabalan, S, Udhayakumar, K. Supersonic jet control by tabs with slanted perforation. Int J Turbo Jet Engines 2021;38:331–9. https://doi.org/10.1515/tjj-2018-0034.Search in Google Scholar
4. George, WK. Lectures in turbulence for the 21st century. Gothenburg, Sweden: Chalmers University of Technology; 2013:65 p.Search in Google Scholar
5. Bradbury, LJS, Khadem, AH. The distortion of a jet by tabs. J Fluid Mech 1975;70:801–13. https://doi.org/10.1017/s0022112075002352.Search in Google Scholar
6. Ahuja, KK, Brown, WH. Shear flow control by mechanical tabs. In 2nd Shear flow conference, March 1989. Tempe, AZ, USA: AIAA Paper; 1989:89–0994 p.10.2514/6.1989-994Search in Google Scholar
7. Sreejith, RB, Rathakrishnan, E. Cross-wire as passive device for supersonic jet control. Reston, VA, USA: AIAA Paper; 2002:2002–4052 p.Search in Google Scholar
8. Tide, PS, Srinivasan, K. Effect of chevron count and penetration on the acoustic characteristics of chevron nozzles. Appl Acoust 2010;71:201–20. https://doi.org/10.1016/j.apacoust.2009.08.010.Search in Google Scholar
9. Mohanta, PK, Sridhar, BTN. Study of decay characteristics of hexagonal and square supersonic jet. Int J Turbo Jet Engines 2017;34:115–22. https://doi.org/10.1515/tjj-2016-0001.Search in Google Scholar
10. Manigandan, S, Vijayaraja, K. Flow mixing and screech characteristics of elliptical supersonic jet. Int J Turbo Jet Engines 2021;38:193–201. https://doi.org/10.1515/tjj-2018-0006.Search in Google Scholar
11. Gopinath, S, Sundararaj, M, Elangovan, S, Sridhar, BTN. Effect of swirling secondary flow on the under-expanded non-circular supersonic jets. Int J Turbo Jet Engines 2021;38:41–9. https://doi.org/10.1515/tjj-2017-0047.Search in Google Scholar
12. Han, SY, Taghavi, RR, Farokhi, S. Passive control of supersonic rectangular jets through boundary layer swirl. Int J Turbo Jet Engines 2013;30:199–216. https://doi.org/10.1515/tjj-2013-0012.Search in Google Scholar
13. Sureshkumar, A, Sridhar, BTN. Experimental studies on decay and spread characteristics of an over expanded triangular supersonic jet. Fluid Dynam 2019;54:629–39. https://doi.org/10.1134/s0015462819050082.Search in Google Scholar
14. Sureshkumar, A, Sridhar, BTN. Axial flow development characteristics of circular and triangular supersonic jets in the presence of an annular coflow at large separation distance. Proc IME G J Aero Eng 2020;234:804–17. https://doi.org/10.1177/0954410019887631.Search in Google Scholar
15. Mariani, R, Kontis, K. Effects of exit nozzle diameter on compressible vortex rings flow structure. In: 47th AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition, Orlando, FL, USA; 2009. https://doi.org/10.2514/6.2009-410.10.2514/6.2009-410Search in Google Scholar
16. Mi, J, Nathan, GJ, Luxton, RE. Centerline mixing characteristics of jets from nine differently shaped nozzles. Exp Fluid 2000;28:93–4. https://doi.org/10.1007/s003480050012.Search in Google Scholar
17. Quinn, WR. Measurements in the near flow field of an isosceles triangular free jet. Exp Fluid 2005;39:111–26. https://doi.org/10.1007/s00348-005-0988-2.Search in Google Scholar
18. Zaman, KBMQ. Spreading characteristics of compressible jets from nozzles of various geometries. J Fluid Mech 1999;383:197–228. https://doi.org/10.1017/s0022112099003833.Search in Google Scholar
19. Gutmark, E, Schadow, KC, Wilson, KJ. Subsonic and supersonic combustion using noncircular injectors. J Propul Power 1991;27:240–9. https://doi.org/10.2514/3.23317.Search in Google Scholar
20. Mohanta, PK, Sridhar, BTN. Study of decay characteristics of rectangular and elliptical supersonic jets. Therm Sci 2017;21:3001–10. https://doi.org/10.2298/tsci151224214m.Search in Google Scholar
21. Mohanta, PK, Sridhar, BTN. Effect of hydraulic diameter on potential core decay of supersonic jets. INCAS Bull 2020;12:119–26. https://doi.org/10.13111/2066-8201.2020.12.1.11.Search in Google Scholar
22. Ilakkiya, S, Sridhar, BTN. An experimental study on the effect of square grooves on decay characteristics of a supersonic jet from a circular nozzle. J Mech Sci Technol 2018;32:4721–9. https://doi.org/10.1007/s12206-018-0919-9.Search in Google Scholar
23. http://www.meas-spec.com/product/tm_product.aspx?id=9290.Search in Google Scholar
24. Pao, SP, Abdol-Hamid, KS. Numerical simulation of jet aerodynamics using the three-dimensional Navier-Stokes code PAB3D, NASA Technical Paper 3596. Hampton, Virginia, USA: National Aeronautics and Space Administration Langley Research Center; 1996. http://techreports.larc.nasa.gov/ltrs/ltrs.html.Search in Google Scholar
25. Rathakrishnan, E. Instrumentation, measurements, and experiments in fluids, 2nd ed. 6000 Broken Sound Parkway NW, Suite 300, Boca Raton, FL 33487-2742: CRC Press, Taylor & Francis Group; 2017.Search in Google Scholar
© 2021 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Characterization of titanium grade 5 alloy compressor blade in a jet engine using advanced materials for optimum thrust production
- Numerical investigation of total temperature distortion problem in a multistage fan based on body force approach
- Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine
- Baseline architecture design for a turboelectric distributed propulsion system using single turboshaft engine operational scenario
- Active fault tolerant control of turbofan engines with actuator faults under disturbances
- Modeling and mode transition simulation of over-under turbine based combined cycle (TBCC) propulsion system based on inlet/engine matching
- Numerical analysis of high temperature gas flow through conical micronozzle
- Simulation and analysis of an aero-engine combustor with a slinger fuel injection system
- Influence of plasma-chemical products on process stability in a low-emission gas turbine combustion chamber
- Influence of nozzle exit geometrical parameters on supersonic jet decay
- Experimental investigation on mixing characteristics of high speed co-flow jets by using tabbed chevron nozzle
- Study of a new effervescent atomizer design
Articles in the same Issue
- Frontmatter
- Characterization of titanium grade 5 alloy compressor blade in a jet engine using advanced materials for optimum thrust production
- Numerical investigation of total temperature distortion problem in a multistage fan based on body force approach
- Life assessment of a high temperature probe designed for performance evaluation and health monitoring of an aero gas turbine engine
- Baseline architecture design for a turboelectric distributed propulsion system using single turboshaft engine operational scenario
- Active fault tolerant control of turbofan engines with actuator faults under disturbances
- Modeling and mode transition simulation of over-under turbine based combined cycle (TBCC) propulsion system based on inlet/engine matching
- Numerical analysis of high temperature gas flow through conical micronozzle
- Simulation and analysis of an aero-engine combustor with a slinger fuel injection system
- Influence of plasma-chemical products on process stability in a low-emission gas turbine combustion chamber
- Influence of nozzle exit geometrical parameters on supersonic jet decay
- Experimental investigation on mixing characteristics of high speed co-flow jets by using tabbed chevron nozzle
- Study of a new effervescent atomizer design
