Effect of Secondary Injection Reaction Thermal Resistance on Thrust Vector Control in Divergent Section

Cheng, Yang; Wang, Ningfei; Xie, Kan; Guo, Changchao

doi:10.2514/6.2018-4485

Cited by 2 publications

(2 citation statements)

References 10 publications

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“…The effect of secondary injection reaction heat on TVC was also explored computationally and experimentally. For primary and secondary flow, methane and air reaction were used for the reaction process [59]. The effect of the different gas injectors on the main nozzle was investigated.…”

Section: Injectorsmentioning

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: Injectorsmentioning

confidence: 99%

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

Afridi,

Khan,

Shah

et al. 2023

Energies

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“…By injecting an oxidizing gas (such as pure oxygen or air) into the throat of the nozzle, the primary flow undergoes preburning, resulting in increased heat release and improved thermal resistance of the nozzle's throat. This, in turn, enhances the nozzle's choke performance and thrust regulation ratio [9,26,27].…”

Section: Introductionmentioning

confidence: 98%

Study on the Effect of Oxidative Jet and Vortex Structure in Fluidic Throat Combined with Thrust Vector Control

Yan

Xiao

et al. 2023

International Journal of Aerospace Engineering

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To examine the impact of oxidative jets on the thrust vector angle, secondary combustion efficiency, and combustion chamber pressure, inert gas (nitrogen) and pure oxygen are injected into the primary flow, which includes combustible components, at various locations in the divergence section and throat using different injection techniques. The simulations utilize Reynolds-averaged Navier-Stokes equations coupled with the SST k - ω turbulence model in two-dimensional numerical simulations and large-eddy simulation in three-dimensional studies. The numerical method is validated through schlieren experiments, and the vortex is identified using the Liutex-Omega method. The vortex structures and flow characteristics are analyzed. The results indicate that, at the same flow rate, the vector control effect of pure oxygen is superior to nitrogen only in the divergence section, but inferior to nitrogen in both the divergence section and throat. However, with improved vector control, the peak of the vector angle is achieved at a lower flow rate in the case of pure oxygen. When the secondary flow is introduced only in the divergence section, the flow ratio corresponding to the peak point in the pure oxygen case is approximately 14.3% earlier than that in the nitrogen case. The introduction of the pure oxygen jet enhances the secondary combustion efficiency of the primary flow, but to a limited extent. Additionally, when the jet is introduced at the throat, the effect of the pure oxygen case on adjusting the combustion chamber pressure is inferior to that of the nitrogen case. Concerning flow details, the trailing lower vortex replaces the trailing major vortex to become the highest magnitude vortex when the momentum flux ratio is small.

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Effect of Secondary Injection Reaction Thermal Resistance on Thrust Vector Control in Divergent Section

Cited by 2 publications

References 10 publications

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

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

Study on the Effect of Oxidative Jet and Vortex Structure in Fluidic Throat Combined with Thrust Vector Control

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