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.

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Fig. 1

Sketch of the dual throat fluidic thrust vectoring nozzle

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Fig. 2

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

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Fig. 3

Comparison of experimental and computational upper-wall pressure

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Fig. 4

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

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Fig. 5

Pressure distributions of different grids on the upper-wall

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Fig. 6

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

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Fig. 7

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

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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.

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Fig. 9

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

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Fig. 10

Sketch of vortex interaction in the DTN




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