Experimental and Numerical Investigations of a Bypass Dual Throat Nozzle

Gu, Rui; Xu, Jianzhong; Guo, Shuai

doi:10.1115/1.4026943

Cited by 49 publications

(58 citation statements)

References 16 publications

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“…15,16 However, the results of this study demonstrated that the thrust efficiency of the nozzle was not enhanced because of the normal shock wave located in the cavity. Other computational and experimental researches were also executed [17][18][19] and a twodimensional (2D) divergent DTN was investigated to acquire large thrust vector angles. [19][20][21] For the divergent DTN, as the NPR increases, the normal shock wave begins to appear and moves downstream, but remains inside the cavity.…”

Section: Introductionmentioning

confidence: 99%

“…Other computational and experimental researches were also executed [17][18][19] and a twodimensional (2D) divergent DTN was investigated to acquire large thrust vector angles. [19][20][21] For the divergent DTN, as the NPR increases, the normal shock wave begins to appear and moves downstream, but remains inside the cavity. In addition, the shock wave structure is not changed with the increase of in the NPR.…”

Section: Introductionmentioning

confidence: 99%

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Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Wang

Huang

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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The dual throat nozzle achieves higher thrust vectoring efficiencies and lesser thrust loss than other fluidic thrust-vectoring nozzles. Separation always occurs at the bottom of the cavity with complex three-dimensional characteristics for the dual throat nozzle. In this paper, by comparing the flow structure, nozzle surface static pressure distributions and skin friction lines, which are obtained by numerical simulations and wind tunnel experiments, an axisymmetric divergent dual throat nozzle is investigated in detail. The main results show the following findings. (1) The experimental schlieren photographs confirm again that the divergent nozzle configuration has the starting problem from an intuitive perspective. Meanwhile, the flow structure and nozzle surface static pressure distributions obtained by numerical simulations are consistent with the experimental results, except for the low nozzle pressure ratios. (2) The circumferential pressure difference is negligible upstream of the separation line but obvious downstream of the separation line. The skin friction lines and nozzle surface static pressure distributions of different circumferential angles obtained by experiments both prove that the actual flow in the axisymmetric divergent dual throat nozzle indeed possesses three-dimensional characteristics. Therefore, it is necessary to utilize the full three-dimensional computational domain to study the complex three-dimensional characteristics of the flow for the axisymmetric divergent dual throat nozzle thoroughly.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Wang

Huang

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…Later, a new kind of FTVC nozzle called by bypass dual-throat nozzle was established and investigated. Gu et al 11 carried out the numerical and experimental studies on steady characteristics of the bypass dual-throat nozzle. It was evident that it can offer the higher thrust efficiencies in some operating conditions, compared with other FTVC methods.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on the shock vector control in a rectangular supersonic nozzle

Kim

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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In recent decades, the fluidic thrust vector control technique is one of the core strategies to redirect various aerospace vehicles, such as modern launch rockets, supersonic aircraft, and guided missiles. The fundamental theory of the shock vector control is that the gas is injected into the supersonic part of a conventional convergent–divergent nozzle from the transverse to cause interactions between the shock waves and boundary layers. Then, the deflection of the primary jet can be easily realized by the induced oblique shock waves. It was evident that the shock vector control is a very simple, low weight, low cost, and quick vectoring response technique to gain high thrust vectoring performance. In the present work, computational fluid dynamics studies were performed at different control parameters in a three-dimensional rectangular supersonic nozzle with the slot injector. For the validation of the numerical methodology, computational results were compared with experimental data referred to the NASA Langley Research Center. The static pressure distributions along the upper and lower nozzle surfaces in the symmetry plane were matched with the test data excellently. Numerical simulations were based on the well-assessed shear stress transport k–ω turbulence model. Second-order accuracy was selected to reveal more details of the flow-field as much as possible. Lots of factors were investigated, such as the momentum flux ratio, length-to-width ratio, injection location, and injection angle. The performance variations for different affecting factors were illustrated and some constructive conclusions were obtained to provide the reference for further investigations in fluidic thrust vector control field.

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“…While modern fluidic nozzles are designed and developed to increase the thrust vectoring efficiency (14) , to the author's knowledge, limited academic research has been performed on fluidic nozzles, especially multi-directional cylindrical ones. In general, parameters that affect the flow ability to remain attached to the curved surface include the free-stream velocity, radius of curvature, slot location and size (height and span) and blowing pressure (15) .…”

Section: Introductionmentioning

confidence: 99%

An investigation of empirical formulation and design optimisation of co-flow fluidic thrust vectoring nozzles

Banazadeh

Saghafi

2016

Aeronaut. j.

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The purpose of this paper is to design and develop an advanced co-flow fluidic nozzle, based on the Coanda effect concept, for multi-directional thrust vectoring of small jet engines. Recent progress on finding an optimal geometry with a fixed momentum ratio to achieve maximum thrust deflection angle is discussed here. The efficiency of the system is found to be a weakly nonlinear function of the secondary to primary flow momentum as well as three geometric parameters. A useful empirical formulation is derived for thrust vectoring angle, based on a series of tests carried out on different nozzles. An accurate computational fluid dynamics model is also developed and evaluated against the experimental data. Moreover, quasi-Newton optimisation algorithm is employed to find an optimal geometry with a constant relative jet momentum and a constant secondary slot size. In this technique, the optimal wall geometric parameters are calculated in the direction of the steepest gradient with the help of the numerical simulation model in every iteration step. Additionally, an optimised fluidic nozzle is constructed to experimentally verify the numerical results and the empirical equation.

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Experimental and Numerical Investigations of a Bypass Dual Throat Nozzle

Cited by 49 publications

References 16 publications

Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Experimental and numerical investigation of an axisymmetric divergent dual throat nozzle

Numerical study on the shock vector control in a rectangular supersonic nozzle

An investigation of empirical formulation and design optimisation of co-flow fluidic thrust vectoring nozzles

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