Supersonic Jet Control by Tabs with Slanted Perforation
-
G. Ezhilmaran
,
Suresh Chandra Khandai
Abstract
Control of Mach 1.8 circular jet with slanted perforated tabs is studied experimentally. Two sets of perforated tabs were used for this study. The perforation angles were 0° and 30° with respect to axis of the nozzle. The blockage areas of the tabs were 5 %. The mixing enhancements caused by these tabs were studied in the presence of adverse and favorable pressure gradients, corresponding to nozzle pressure ratio (NPR) of 4, 5.74 and 8. For Mach number 1.8, jet NPR 4 corresponds to 30 % adverse pressure gradients and NPR 8 corresponds to 39.37 % favorable pressure gradients. The pressure decay characteristics and shadowgraph images of perforated tabs at different NPR were compared. There is 45 % and 65 % reduction in jet core length were observed for the 0° and 30° perforated tabs respectively in both pitot and shadowgraph experiments in comparison to uncontrolled jet.
Future Work
Effectiveness of present tab geometry with jets issuing from non-circular nozzles can be studied experimentally. Further Research can be carried out for the tabs with Slanted perforation at other supersonic Mach numbers. Also, tab shape and thickness can be considered as parameters for further study.
Acknowledgements
The financial support provided by University Grants Commission, India (No. F MRP 6149/15, SERO/UGC) is gratefully acknowledged.
Nomenclature
- AR
Aspect ratio
- C-D
Convergent-Divergent
- NPR
Nozzle pressure ratio
- CN
Circular nozzle without tab
- CNWTSH
Circular nozzle with straight perforated tab
- CNWST
Circular nozzle with slanted perforated tab
Throat diameter, mm
- D
Exit diameter, mm
Atmospheric pressure
Exit pressure
Exit Mach number
- P
Pressure measured by pitot tube
Stagnation chamber pressure
Total temperature in the settling chamber
Core length,mm
Percentage core length reduction
- γ
Ratio of specific heats.
- L
Length of the tab, mm
- W
Width of the tab, mm
Diameter of the perforation in the tab, mm
References
1. Bradbury LJS, Khadem AH. The distortion of a jet by tabs. J Fluid Mech. 1975;70:801–13.10.1017/S0022112075002352Search in Google Scholar
2. Vishnu J, Rathakrishnan E. Acoustic characteristics of supersonic jets from grooved nozzles. J Propul Power. 2004;20:520–26.10.2514/1.4447Search in Google Scholar
3. Akram S, Rathakrishnan E. Control of supersonic elliptic jet with ventilated tabs. Int J Turbo Jet Engines. 2017;0:2017–33.10.1515/tjj-2017-0033Search in Google Scholar
4. Aravindh Kumar SM, Rathakrishnan E. Rectangular tabs for elliptic jet control. International Conference on Fluid Power and Mechatronics (FPM). 2015; 1399–407.10.1109/FPM.2015.7337340Search in Google Scholar
5. Ahmed RA, Thanigaiarasu S, Kannah DLVV, Elangovan S, Rathakrishnan E. Effect of Slanted Perforation in Tabs for Subsonic and Transonic Jets. In: Saha A, Das D, Srivastava R, Panigrahi P, Muralidhar K. (eds.) Fluid Mechanics and Fluid Power – Contemporary Research. Lecture Notes in Mechanical Engineering. Springer, New Delhi, ISSN 2195-4356, 2017;795–809.10.1007/978-81-322-2743-4_75Search in Google Scholar
6. Dharmahinder SC, Thanigaiarasu S, Elangovan S, Rathakrishnan E. Perforated arc-tabs for jet control. Int J Turbo Jet-Engines. 2011;28:133–38.10.1515/tjj.2011.012Search in Google Scholar
7. Berrueta T, Rathakrishnan E. Control of subsonic and sonic jets with limiting tabs. Int J Turbo Jet Eng. 2017;34:103–13.10.1515/tjj-2016-0037Search in Google Scholar
8. Khandai SC, Parammasivam KM. Experimental study of single expansion ramp nozzle flows (SERN) at low supersonic speeds. Int J Mech Mechatron Eng IJMME-IJENS. 2014;14: 84–89.Search in Google Scholar
9. Rathakrishnan E. Instrumentation, measurements and experiments in fluids, Boca Raton, FL: CRC Press, 2017.10.1201/b15874Search in Google Scholar
10. Lovaraju P, Rathakrishnan E. Subsonic and transonic jet control with cross-wire. AIAA J. 2006;44:2700–05.10.2514/6.2005-3504Search in Google Scholar
© 2018 Walter de Gruyter GmbH, Berlin/Boston
Articles in the same Issue
- Frontmatter
- Effect of orifice spacing on twin circular parallel compressible jets
- Design and Experiment of Casing Treatment for a Centrifugal Compressor
- An Integrated Throughflow Method for the Performance Analysis of Variable Cycle Compression Systems
- Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps
- Study on a Quasi-Two-Dimensional Fan Model for Variant Bypass-Ratio Condition
- Co-Flowing Jet Control Using Lip Thickness Variation
- Investigation on the Effect of Different Lands on Trailing Edge Slot Film Cooling
- Installation Characteristics of Variable Cycle Engine Based on Inlet Flow Matching
- Supersonic Jet Control by Tabs with Slanted Perforation
- Effect of Injection Angle on Performance of Full Coverage Film Cooling with Opposite Injection Holes
Articles in the same Issue
- Frontmatter
- Effect of orifice spacing on twin circular parallel compressible jets
- Design and Experiment of Casing Treatment for a Centrifugal Compressor
- An Integrated Throughflow Method for the Performance Analysis of Variable Cycle Compression Systems
- Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps
- Study on a Quasi-Two-Dimensional Fan Model for Variant Bypass-Ratio Condition
- Co-Flowing Jet Control Using Lip Thickness Variation
- Investigation on the Effect of Different Lands on Trailing Edge Slot Film Cooling
- Installation Characteristics of Variable Cycle Engine Based on Inlet Flow Matching
- Supersonic Jet Control by Tabs with Slanted Perforation
- Effect of Injection Angle on Performance of Full Coverage Film Cooling with Opposite Injection Holes
