Multi-objective nozzle design optimization for maximum thrust vectoring performance

Afridi, Saadia; Khan, Tariq Amin

doi:10.1177/09544100221106656

Cited by 8 publications

(6 citation statements)

References 31 publications

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“…Optimization of the bypass dual throat nozzle has been carried out by analyzing three aspects of the nozzle parameters. It was found that bypass angle and bypass width have a significant impact on the thrust vectoring performance of the nozzle [126].…”

Section: Effect Of Nprmentioning

confidence: 99%

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Afridi,

Khan,

Shah

et al. 2023

Energies

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Thrust vectoring innovations are demonstrated ideas that improve the projection of aerospace power with enhanced maneuverability, control effectiveness, survivability, performance, and stealth. Thrust vector control systems following a variety of concepts have been considered for modern aircraft and missiles to enhance their military performance. Short Take-off and Landing (STOL) and control effectiveness at lower aircraft speeds can be achieved by employing Fluidic Thrust Vectoring Control (FTVC). This paper summarizes a range of ideas for FTVC that have been designed and tested both computationally and experimentally to determine the thrust vectoring performance of supersonic propulsion system nozzles. The conventional method of thrust vectoring involves mechanical means to deflect the direction of flow of the exhaust gases, whereas the most recent method involves fluidic-based thrust vectoring techniques. Fluid-based thrust vectoring has the advantages of simplicity and low weight over mechanical-based thrust vectoring, which has complex geometry and adds extra weight to the aircraft. The fluidic vectoring control nozzles are divided into seven categories: shock vector, bypass shock vector, counterflow, co-flow, throat skewing, dual throat, and bypass dual throat nozzle control. This paper provides a summary of each fluidic thrust vectoring technique with its characteristics, design, classification, and different operational criteria developed to date and compares the intrinsic characteristics of each technique. Based on the present literature, it is concluded that among all the fluidic control techniques, the bypass dual-throat nozzle control can achieve better thrust vectoring performance with large vector angles and low thrust loss.

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Section: Effect Of Nprmentioning

confidence: 99%

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Afridi,

Khan,

Shah

et al. 2023

Energies

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“…The performance parameters considered are thrust, discharge coefficients, vectoring angle and efficiency. Thrust vectoring parameter is calculated as [49],…”

Section: Ftv Performance Parameters Consideredmentioning

confidence: 99%

Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

et al. 2023

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Modern aircraft and missiles are gradually integrating thrust vector control systems to enhance their military capabilities. Bypass Dual-Throat Nozzle (BDTN) control is a new fluidic thrust vectoring technique capable of achieving superior performance with large vector angles and low thrust loss. In this study, we analyzed the flow characteristics and performance parameters of BDTN by varying the bypass angle, nozzle convergence angle, and bypass width. The flow governing equations are solved according to a finite volume discretization technique of the compressible RANS equations coupled with the Renormalization Group (RNG) k-ϵ turbulence model for Nozzle Pressure Ratio (NPR = 2~10) to capture the significance of under-expanded and over-expanded jets. Results show that by decreasing the bypass angle from 90° to 35°, there is a 6% increase in vectoring angle while the vectoring efficiency is enhanced by 18%. However, a decrease of 3% in the thrust and discharge coefficients is also observed. When the convergence angle was increased from 22° to 37°, vectoring angle, discharge coefficient, and thrust coefficient increased by 2%, 1%, and 0.26%, respectively. Moreover, vectoring efficiency is also enhanced by 8% by reducing the convergence angle from 37° to 22°. Based on the investigated parameters, it is determined that nozzle convergence angle does not significantly influence thrust vectoring performance, however, bypass width and bypass angle have a significant effect on thrust vectoring performance.

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“…Firstly, the internal flow field is calculated by using numerical simulations, and the experimental values are verified. Then, the performance of the swirling–straight composite nozzle is compared with those of the pressure swirl nozzle and the straight jet nozzle 18,19 . Finally, the influence of the straight jet aperture on the performance is analyzed, which provides guidance for the design optimization of the swirling–straight composite nozzle 20 …”

Section: Introductionmentioning

confidence: 99%

A study on the performance of a swirling–straight composite nozzle

Yu,

Li,

Zhang

et al. 2024

Asia-Pacific J Chem Eng

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The nozzle is the key component of water mist fire extinguishing system. As a response to the problems of small injection angle associated with straight jet nozzles and the weak axial momentum of swirl nozzles, a swirling–straight composite nozzle is designed in this work. The comparison with a straight jet nozzle and a pressure swirl nozzle shows that the swirling–straight composite nozzle has a larger axial momentum and better injection angle. Under the same pressure, the volume flow of the swirling–straight composite nozzle is more than 27% of the pressure swirl nozzle, and the injection angle was more than 65% of straight jet nozzle. The numerical model of the swirling–straight composite nozzle is established. Meantime, the internal flow field characteristics and the influence of the straight jet aperture on the performance are studied. The results demonstrate that the straight jet fluid and swirling fluid can be mixed well in the nozzle, and a larger axial momentum and tangential momentum can be obtained. With the increase of the straight jet aperture, the swirl effect in the nozzle becomes weaker, the injection angle becomes smaller, and the axial momentum improves. When the straight jet aperture increases from 1.1 to 1.9 mm, the straight jet volume flow at the nozzle inlet increases by 127%, and the injection angle reduces by 40%.

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Multi-objective nozzle design optimization for maximum thrust vectoring performance

Cited by 8 publications

References 31 publications

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Techniques of Fluidic Thrust Vectoring in Jet Engine Nozzles: A Review

Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

A study on the performance of a swirling–straight composite nozzle

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