Hostname: page-component-cb9f654ff-d5ftd Total loading time: 0 Render date: 2025-08-09T22:28:33.708Z Has data issue: false hasContentIssue false
  • English
  • Français

Experimental and computationalinvestigation into the use of co-flow fluidic thrustvectoring on a small gas turbine

Published online by Cambridge University Press:  03 February 2016

A. Banazadeh ,
F. Saghafi ,
M. Ghoreyshi  and
P. Pilidis
A. Banazadeh
Affiliation:
Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran
F. Saghafi
Affiliation:
Department of Aerospace Engineering, Sharif University of Technology, Tehran, Iran
M. Ghoreyshi
Affiliation:
Propulsion and Power, School of Engineering, Cranfield University, Bedford, UK
P. Pilidis
Affiliation:
Propulsion and Power, School of Engineering, Cranfield University, Bedford, UK
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper presents the application of a relatively newtechnique of fluidic thrust-vectoring (FTV), namedCo-flow, for a small gas-turbines. The performanceis obtained via experiment and computational fluiddynamics (CFD). The effects of a few selectedparameters including the engine throttle setting,the secondary air mass-flow rate and the secondaryslot height upon thrust-vectoring performance areprovided. Thrust vectoring performance ischaracterised by the ability of the system todeflect the engine thrust with respect to thedelivered secondary air mass-flow rate. Theexperimental study was conducted under staticconditions in an outdoor environment at CranfieldUniversity workshop that was especially designed forthis purpose. As part of this investigation, thesystem was modelled by CFD techniques, usingPointwise’s Gridgen software and thethree-dimensional flow solver, Fluent. Also,Cranfield’s gas-turbine performance code(TurboMatch) was utilised to estimate boundaryconditions for the CFD analysis with respect to theintegrated nozzle. The presented technique iseasy-to-use approach and offers better result forthrust-vectoring problems than previously publishedworks. Experimental results do show the overallviability of the blowing slot mechanism as a meansof vectoring the engine thrust, with the currentconfiguration. Computational predictions are shownto be consistent with the experimental observationsand make the CFD model a reliable tool forpredicting Co-flow fluidic thrust-vectoringperformance of similar systems.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 112 , Issue 1127 , January 2008 , pp. 17 - 25
Copyright
Copyright © Royal Aeronautical Society 2008 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Article purchase

Temporarily unavailable

References

1. Granasy, P., Thrust vectoring at high angle of attack, AIAA Aircraft Engineering, 1st, Technology and Operations Congress, 19-21 September 1995, Los Angeles, CA.Google Scholar
2. Fuelhas, K. and Neubauer, M., Influence of thrust vectoring system (TVS) on structural design loads, Daimler-Benz Aerospace A.G, Loads and requirements for military aircraft, (SEE N97-27983 01-01), Germany, 1997.Google Scholar
3. Berrier, B.L. and Rchard, R.J., A review of thrust-vectoring schemes for fighter applications, 25-27 July 1978, 14th Joint Propulsion Conference, Las Vegas, Nevada.Google Scholar
4. Visser, H.G., Windshear recovery using thrust vectoring, Aircraft Engineering and Aerospace Technology, 1999, 71, (4).Google Scholar
5. Lewis, R., Optimization of a Thrust Vectoring System for a Next Generation Fighter Aircraft, MSc Thesis, 2004, Cranfield University.Google Scholar
6. Curtin, R.J., Thrust Vectoring for Longitudinal Flight Control, MSc Thesis, 2004, Cranfield University.Google Scholar
7. Jimenez, A., Trust vectoring for advanced fighter aircraft, propulsion package development, 8-11 July 2001, AIAA-2001-3991, 37th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit, Salt Lake City, UT.Google Scholar
8. Hilley, P.E., Wallace, H.W. and Booz, D.E., Study of non-axisym-metric nozzles installed in advanced fighter aircraft, 29 September-1 October, 1975, American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, 11th Propulsion Conference, Anaheim, CA.Google Scholar
9. Bergman, D., Mace, J.L. and Thayer, E.B., Non-axisymmetric nozzle concepts for an F-111 test bed, 11-13 July 1977, American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, 13th Propulsion Conference, Orlando.Google Scholar
10. Bowers, A.H., Noffz, G.K. and Grafton, S.B., Multiaxis thrust vectoring using axisymmetric nozzles and postexit vanes on an F/A-18 configuration vehicle, 1991, NASA Technical Memorandum 101741.Google Scholar
11. Kowal, H.J., Advances in thrust vectoring and the application of flow-control technology, Canadian Aero and Space J, 2002, 48, (2), pp 145–151.Google Scholar
12. Flamm, J.D., Experimental study of a nozzle using fluidic counterflow for thrust vectoring, 13-15 July 1998, AIAA paper 1998-3255, AIAA/ASME/SAE/ASEE 34th Joint Propulsion Conference and Exhibit, Cleveland, OH.Google Scholar
13. Strykowski, P.J., Schmid, G.F., Alvi, F.S. and Krothapalli, A., Vectoring thrust using confined countercurrent shear layers, 29 June -2-July 1997, AIAA 28th Fluid Dynamics Conference, Snowmass Village, CO.Google Scholar
14. Strykowski, P.J. and Krothapalli, A., The countercurrent mixing layer — strategies for shear-layer control, 6–9 July 1993, AIAA, Shear Flow Conference, Orlando, FL.Google Scholar
15. Mason, M.S, and Crowther, W.J, Fluidic thrust vectoring of low observable aircraft, June 2002, CEAS Aerospace Research Conference, Cambridge, pp 10–12.Google Scholar
16. Deere, K., Summary of fluidic thrust vectoring research conducted at NASA Langley Research Center, 23-26 June 2003, 21st AIAA Applied Aerodynamics Conference, Orlando, FL.Google Scholar
17. Smith, B.L. and Glezer, A., Vectoring and small-scale motions effected in free shear flows using synthetic jet actuators, 6–9 January 1997, AIAA, 35th, Aerospace Sciences Meeting and Exhibit, Reno, NV, Paper No 97-0213.Google Scholar
18. Deere, K.A., Berrier, B.L., Flamm, J.D. and Johnson, S.K., A computational study of a new dual throat fluidic thrust vectoring nozzle concept, 10-13 July 2005, 41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit; Tucson, AZ.Google Scholar
19. Veodisch, A., Analytical investigation of the Coanda effect (Project No FP-188), April 1947, Air Material Command, Wright Field, Dayton, OH, Rept. F TR-2155-ND.Google Scholar
20. Triboix, A. and Marchal, D., Stability analysis of the mechanism of jet attachment to walls, Int J of Heat and Mass Transfer, 2002, 45, pp 2769–2775.Google Scholar
21. Wikipedia (the free encyclopedia), “Henri Marie Coanda”, http://en.wikipedia.org/wiki/Henri_Coand%C4%83, [cited 4 April 2007].Google Scholar
22. Joslin, R.D. and Jones, G.S., Applications of circulation control technology, Progress in Astro and Aeron, AIAA, Reston, Virginia, 2006, Chps 2 and 9.Google Scholar
23. AMT Netherlands, ‘Olympus Specifications’, http://www.amtjets.com/, [cited 4 April 2007].Google Scholar
24. Ghoreyshi, M., Computational and Experimental Performance Analysis of an Integrated UAV Engine with Fluidic Thrust Vectoring, 2007, PhD Dissertation, Cranfield University.Google Scholar
25. Futek Advanced Sensor Technology, ‘Futek LSM400’ http://www.futek.com/product.aspx?t=load&m=lsm400, [cited 10 April 2007].Google Scholar
26. Fluent, ‘Fluent 6 User Manual’, http://www.fluent.com/software/fluent/index.htm, [cited 6 April 2007].Google Scholar
27. Versteeg, H.K. and Malalasekera, W., An introduction to computational fluid dynamics, the finite volume method, 1995, Prentice Hall, Longman Group, Chp 3.Google Scholar
28. Pointwise, ‘Gridgen v15’, http://www.pointwise.com/gridgen, [cited 14 April 2007].Google Scholar
29. Ghoreyshi, M., Pilidis, P. and Ramsden, K.W., Diagnostics of a small jet engine — neural network approach, 6–9 June 2005, Proceeding of ASME Turbo Expo 2005, Reno-Tahoe, US.Google Scholar
30. TurboMatch, User’s manual: The TurboMatch scheme, for aero/industrial gas turbine engine design point/off-design performance calculation, 2004, Thermal Power Group, Cranfield University, UK.Google Scholar