Design and Preliminary Analysis of the Variable Axisymmetric Divergent Bypass Dual Throat Nozzle

Wang, Yangsheng; Xu, Jinglei; Huang, Shuai; Jiang, Jintao; Pan, Ruifeng

doi:10.1115/1.4045996

Cited by 14 publications

(9 citation statements)

References 19 publications

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“…Specifically, at NPR=10, the bypass DTN achieves a vectoring angle of 21.3 degrees. In continuation of bypass DTN researches, Wang et al (2020a) and Wang et al (2020b) investigated an axisymmetric DTN. Their results showed that a maximum thrust ratio of 0.94 and a maximum vectoring angle of 19.52 degrees are achieved at NPR=4.47, while discharge coefficient having a value of 0.97.…”

Section: A New Fluidic Technique Has Been Developed Bymentioning

confidence: 99%

Computational Investigation of Effects of Side-Injection Geometry on Thrust-Vectoring Performance in a Fuel-Injected Dual Throat Nozzle

2022

JAFM

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Dual-throat Nozzle (DTN) is known as one of the most effective approaches of fluidic thrust-vectoring. It is gradually flourishing into a promising technology to implement supersonic and hypersonic thrust-vector control in aircrafts. The main objective of the present study is numerical investigation of the effects of secondary injection geometry on the performance of a fuel-injected planar dual throat thrust-vectoring nozzle. The main contributions of the study is to consider slot and circular geometries as injector cross-sections for injecting four different fuels; moreover, the impact of center-to-center distance of injection holes for circular injector is examined. Three-dimensional compressible reacting simulations have been conducted in order to resolve the flowfield in a dual throat nozzle with pressure ratio of 4.0. Favre-averaged momentum, energy and species equations are solved along with the standard k − ε model for the turbulence closure, and the eddy dissipation model (EDM) for the combustion modelling. Second-order upwind numerical scheme is employed to discretize and solve governing equations. Different assessment parameters such as discharge coefficient, thrust ratio, thrust-vector angle and thrust-vectoring efficiency are invoked to analyze the nozzle performance. Computationally predicted data are agreed well with experimental measurements of previous studies. Results reveal that a maximum vector angle of 17.1 degrees is achieved via slot injection of methane fuel at a secondary injection rate equal to 9% of primary flow rate. Slot injection is performing better in terms of discharge coefficient, thrust-vector angle and thrust-vectoring efficiency, whereas circular injection provides higher thrust ratio. At 2% secondary injection for methane fuel, vector angle and vectoring efficiency obtained by slot injector is 8% and 34% higher than the circular injector, respectively. Findings suggest that light fuels offer higher thrust ratio, vector angle and vectoring efficiency, while heavy fuels have better discharge coefficient. Increasing center-to-center distance of injector holes improves thrust ratio, while having a negative effect on discharge coefficient, vector angle and vectoring efficiency. A comparison between fuel injectant of current study and inert injectant in the previous studies indicates that fuel reaction could exhibit substantial positive effects on vectoring performance. Secondary-to-primary momentum flux ratio is found to play a crucial role in nozzle performance.

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Section: A New Fluidic Technique Has Been Developed Bymentioning

confidence: 99%

Computational Investigation of Effects of Side-Injection Geometry on Thrust-Vectoring Performance in a Fuel-Injected Dual Throat Nozzle

2022

JAFM

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“…Until now, the effect of secondary mass flow modulation, expansion ratio, cavity radius, nozzle throat radius, dynamic vector rate, and dynamic hysteresis time has been investigated in detail. [17][18][19][20][21][22] However, the contribution of nozzle convergence angle with bypass width and bypass angle with bypass width on the bypass dual throat nozzle (BDTN) performance is still unknown. Based on the literature, a BDTN is selected to study the thrust vectoring behavior of the nozzle.…”

Section: Motivation and Organization Of Researchmentioning

confidence: 99%

“…Results indicate that the numerical model can resolve the detailed flow field and that the experimental and numerical results agree well. [17][18][19][20][21][22] Therefore, in the present work, FLUENT is used to solve the governing equations with RNG k-ϵ turbulence modeling to simulate the flow through the proposed geometry configurations. The governing equations including conservation of mass, momentum, and energy equations are written as follows 29 :…”

Section: Computational Fluid Dynamics Flow Solvermentioning

confidence: 99%

“…Best thrust vectoring performance was achieved for these configurations which provided a 50% increase in the throat area. 21,22 A recent study on the shape of the bypass channel indicated that the V-shape bypass passage induces losses in nozzle. In order to minimize losses, the V-shape bypass passage is replaced by an arc-shape bypass passage.…”

Section: Supersonic Nozzle Designmentioning

confidence: 99%

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Multi-objective nozzle design optimization for maximum thrust vectoring performance

Afridi

Khan

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Thrust vectoring is a promising technology that offers the potential for improved maneuverability, control efficiency, and stealth characteristics of aircraft. Optimized nozzle design over a range of operating conditions is one of the most crucial factors for maximum thrust vectoring operation. Our goal was to investigate the optimal design of bypass dual throat nozzle to maximize thrust vectoring. We performed a multi-objective optimization study by varying the nozzle bypass angle, convergence angle, and bypass width to see what impact these parameters had on the performance of the bypass dual throat nozzle. A steady numerical simulation has been performed on 55 different nozzle configurations to compare their thrust vectoring performance and losses. In all simulations, the k- ϵ turbulence model is used to determine the vectoring states of the nozzle. The computational fluid dynamics analysis was followed by a multi-objective optimization process using the Response Surface Methodology within the ModeFrontier software. The testing of the optimized nozzle shapes using ANSYS FLUENT verified the accuracy and reliability of the multi-objective optimization algorithm. These findings suggest that nozzle convergence does not significantly affect thrust vectoring. In contrast, bypass width and bypass angle significantly affected thrust vectoring.

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“…However, when the nozzle number of experimental and numerical studies have been carried out for the DTN method, and an in-depth understanding of its characteristics has been obtained. However, when the nozzle changes from a convergent nozzle to a convergent-divergent nozzle and the NPR increases, the performance of the DTN decreases significantly [8][9][10][11][12][13]. The counter-flow [1,14] method has excellent performance in terms of the thrust coefficient, vector angle, and discharge coefficient.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics of the Novel Two-Dimensional Enhanced Shock Vector Nozzle

Shu,

Gao,

Huang

et al. 2024

Aerospace

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Fluid thrust vectoring (FTV) control has obvious advantages in structural quality and stealth performance because of its fast response and light weight. However, improving FTV vector performance will cause a loss in engine performance due to the need to draw airflow from the engine. In order to alleviate the above problems and further improve the vector performance of FTV, a nozzle combined with throat skewing and shock vector control is proposed, and the secondary flow of the nozzle comes from the throat and is injected into the nozzle divergence section. The numerical results indicate that compared with the original configuration, the vector angle and vector efficiency of the new configuration are more linear with the nozzle pressure ratio (NPR), and the vector angle and vector efficiency are improved by 163% and 218%, respectively, while experiencing a maximum reduction in the thrust coefficient of 1.4%. Compared with the only bypass-type shock vector nozzle, the new configuration utilizes the diversion of the two jets to eliminate the reattachment of the separation bubble after the jet and its resulting abrupt change in vector performance, improving the performance while having good control characteristics. Additionally, a sensitivity analysis of the spacing between two jets is also carried out. The spacing between two jets should be increased to make the flow pass through two weaker shock waves to improve the vector performance while ensuring that the separation after the jet is no longer attached.

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Design and Preliminary Analysis of the Variable Axisymmetric Divergent Bypass Dual Throat Nozzle

Cited by 14 publications

References 19 publications

Computational Investigation of Effects of Side-Injection Geometry on Thrust-Vectoring Performance in a Fuel-Injected Dual Throat Nozzle

Computational Investigation of Effects of Side-Injection Geometry on Thrust-Vectoring Performance in a Fuel-Injected Dual Throat Nozzle

Multi-objective nozzle design optimization for maximum thrust vectoring performance

Aerodynamic Characteristics of the Novel Two-Dimensional Enhanced Shock Vector Nozzle

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