0
Technical Briefs

Effects of Cavity on the Performance of Dual Throat Nozzle During the Thrust-Vectoring Starting Transient Process

[+] Author and Article Information
Rui Gu

e-mail: sz24zxdzb3@126.com

Jinglei Xu

Professor at NUAA
e-mail: xujl@nuaa.edu.cn
Department of Power Engineering,
Nanjing University of Aeronautics and
Astronautics (NUAA),
Nanjing 210016, China

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 3, 2013; final manuscript received July 31, 2013; published online October 21, 2013. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(1), 014502 (Oct 21, 2013) (6 pages) Paper No: GTP-13-1232; doi: 10.1115/1.4025243 History: Received July 03, 2013; Revised July 31, 2013

The dual throat nozzle (DTN) technique is capable to achieve higher thrust-vectoring efficiencies than other fluidic techniques, without compromising thrust efficiency significantly during vectoring operation. The excellent performance of the DTN is mainly due to the concaved cavity. In this paper, two DTNs of different scales have been investigated by unsteady numerical simulations to compare the parameter variations and study the effects of cavity during the vector starting process. The results remind us that during the vector starting process, dynamic loads may be generated, which is a potentially challenging problem for the aircraft trim and control.

FIGURES IN THIS ARTICLE
<>
Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.

References

Walker, S. H., 1997, “Lessons Learned in the Development of a National Cooperative Program,” AIAA Paper No. 97-3348. [CrossRef]
Deere, K. A., 1997, “Summary of Fluidic Thrust Vectoring Research Conducted at NASA Langley Research Center,” AIAA Paper No. 2003-3800. [CrossRef]
Deere, K. A., 2000, “Computational Investigation of the Aerodynamic Effects on Fluidic Thrust Vectoring,” AIAA Paper No. 2000-3598. [CrossRef]
YonhHeo, J., and Sung, H.-G., 2012, “Fluid Thrust-Vector Control of Supersonic Jet Using Coflow Injection,” J. Propul. Power, 28(4), pp. 858–861. [CrossRef]
Miller, D. N., Yagle, P. J., and Hamstra, J. W., 1999, “Fluidic Throat Skewing for Thrust Vectoring in Fixed-Geometry Nozzles,” AIAA Paper No. 99-0365. [CrossRef]
Williams, R. G., and Vittal, B. R., 2002, “Fluidic Thrust Vectoring and Throat Control Exhaust Nozzle,” AIAA Paper No. 2002-4060. [CrossRef]
Shin, C., and Dong Kim, H., 2010, “A Computational Study of Thrust Vectoring Control Using Dual Throat Nozzle,” J. Therm. Sci., 19(6), pp. 486–490. [CrossRef]
Abeyounis, W. K., and Bennett, B. D., Jr., 1997, “Static Internal Performance of an Over Expanded Fixed-Geometry, Nonaxisymmetric Nozzle With Fluidic Pitch-Thrust-Vectoring Capability,” NASA Paper No. TP-3645.
Strykowski, P. J., and Krothapalli, A., 1993, “The Countercurrent Mixing Layer: Strategies for Shear-Layer Control,” AIAA Paper No. 93-3260. [CrossRef]
Flamm, J. D., 1998, “Experimental Study of a Nozzle Using Fluidic Counterflow for Thrust Vectoring,” AIAA Paper No. 98-3255. [CrossRef]
Deere, K.A, 1998, “PAB3D Simulation of a Nozzle With Fluidic Injection For Yaw Thrust-Vector Control,” AIAA Paper No. 98-3254. [CrossRef]
Deere, K. A., Berrier, B. L., Flamm, J. D., and Johnson, S. K., 2005, “A Computational Study of a Dual Throat Fluidic Thrust Vectoring Nozzle Concept,” AIAA Paper No. 2005-3502. [CrossRef]
Flamm, J. D., Deere, K. A., Berrier, B. L., and Johnson, S. K., 2005, “An Experimental Study of a Dual Throat Fluidic Thrust Vectoring Nozzle Concept,” AIAA Paper No. 2005-3503. [CrossRef]
Deere, K. A., Flamm, J. D., Berrier, B. L., and Johnson, S. K., 2007, “Computational Study of an Axisymmetric Dual Throat Fluidic Thrust Vectoring Nozzle for a Supersonic Aircraft Application,” AIAA Paper No. 2007-5085. [CrossRef]
Deere, K. A., Flamm, J. D., Berrier, B. L., and Johnson, S. K.2007, “Experimental Study of an Axisymmetric Dual Throat Fluidic Thrust Vectoring Nozzle Concept for Supersonic Aircraft Application,” AIAA Paper No. 2007-5084. [CrossRef]
Flamm, J. D., Deere, K. A., Mason, M. L., Berrier, B. L., and Johnson, S. K., 2006, “Design Enhancements of the Two-Dimensional, Dual Throat Fluidic Thrust Vectoring Nozzle Concept,” AIAA Paper No. 2006-3701. [CrossRef]
Radhakrishnan, S., and Meganathan, A. J., 2002, “Open Cavity Flow at Subsonic Speeds—Comparison of Numerical Simulations With Experiments,” AIAA Paper No. 2002-0571. [CrossRef]
Li, Z., Li, J., and Yan, X., 2011, “Effects of Pressure Ratio and Rotational Speed on Leakage Flow and Cavity Pressure in the Staggered Labyrinth Seal,” ASME J. Eng. Gas Turbines Power, 133(11), p. 114503. [CrossRef]
Ganine, V., Umesh, J., and Hills, N., 2012, “Coupled Fluid-Structure Transient Thermal Analysis of a Gas Turbine Internal Air System With Multiple Cavities,” ASME J. Eng. Gas Turbines Power, 134(10), pp. 102508. [CrossRef]
Patankar, S. V., 1980, Numerical Heat Transfer and Fluid Flow, McGraw-Hill, New York, pp. 89–109.

Figures

Grahic Jump Location
Fig. 1

Sketch of the dual throat fluidic thrust vectoring nozzle

Grahic Jump Location
Fig. 2

Numerical simulation and experiment results comparison. (a) Experimental shadowgraph image [10]; (b) Mach contour of simulation.

Grahic Jump Location
Fig. 3

Comparison of experimental and computational upper-wall pressure

Grahic Jump Location
Fig. 4

Computational mesh. (a) Computational mesh for the domain; (b) zoomed in computational mesh at the nozzle.

Grahic Jump Location
Fig. 5

Pressure distributions of different grids on the upper-wall

Grahic Jump Location
Fig. 6

Nozzle performance of Case 1 during the vector starting process. (a) Thrust vector angle; (b) discharge coefficient; and (c) thrust coefficient.

Grahic Jump Location
Fig. 7

Nozzle performance of Case 2 during the vector starting process. (a) Thrust vector angle; (b) discharge coefficient; and (c) thrust coefficient.

Grahic Jump Location
Fig. 8

Vorticity contour and velocity vector of Case 2. (a) 1.5 ms; (b) 5 ms; (c) 7 ms; and 8 (d) 10 ms.

Grahic Jump Location
Fig. 9

Pressure contour and velocity vector of Case 2. (a) 1.5 ms; and (b). 5 ms.

Grahic Jump Location
Fig. 10

Sketch of vortex interaction in the DTN

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In