Experimental investigation of serpentine nozzles for turbofan

Hui, Zhonghao; Shi, Jingwei; Li, Zhou; Wang, Zhanxue; Liu, Yongquan

doi:10.1016/j.ast.2021.106892

Cited by 20 publications

(4 citation statements)

References 23 publications

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“…Detailed procedures for the design of serpentine nozzles have been provided in Ref. [34]. The stealth performance and aerodynamic characteristics of serpentine nozzles should be comprehensively considered during the process of structural design.…”

Section: Geometric Modelmentioning

confidence: 99%

A Numerical Investigation of Film Cooling under the Effects of Different Adverse Pressure Gradients

Shi,

Hui,

Zhou

et al. 2024

Aerospace

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Film cooling needs to be applied to serpentine nozzles due to an increase in thermal load. Adverse pressure gradients (APGs) near the upper wall of such nozzles hinder the forward flow of the coolant, and they may even induce a recirculation zone that complicates the cooling of the film in serpentine nozzles under different APGs. In this study, the film cooling characteristics of a serpentine nozzle under various APGs are investigated through numerical simulations. The studied pressure gradients include strong, moderate, and weak APGs. The results show that the APG weakened the adhesion of the coolant to the surface, thereby reducing the film cooling effectiveness (FCE) and the convective heat transfer coefficient (CHTC). The stronger the APG, the greater its obstructive effect. However, the recirculation zone induced by the strong APG was composed of the coolant, and it adhered tightly to the wall, thereby significantly strengthening the FCE and CHTC. The CHTC under the moderate APG significantly increased due to the convergence of two jets ejected from different holes. For the four blowing ratios, the area-averaged FCE under the strong APG was 29.8% and 24.5% higher than that under the moderate and weak APGs, while the area-averaged ratios of the CHTC under the moderate APG were 1.6% and 16.7% higher than those under the strong and weak APGs. Therefore, more holes should be arranged on the film in the zones of moderate and weak APGs.

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Section: Geometric Modelmentioning

confidence: 99%

A Numerical Investigation of Film Cooling under the Effects of Different Adverse Pressure Gradients

Shi,

Hui,

Zhou

et al. 2024

Aerospace

Self Cite

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“…The cooling airflow from the third stream is mixed with the jet after the throat section, effectively reducing the infrared radiation characteristics of the exhaust system. Consequently, the design of adaptive cycle engines necessitates the consideration of not only thrust performance and fuel consumption but also the infrared radiation intensity emitted by the engine exhaust system [14][15][16][17][18][19]. The traditional overall design method for engines no longer aligns with these requirements, highlighting the urgency to develop a comprehensive design approach for adaptive cycle engines with low infrared characteristics.…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective Optimization Design of Adaptive Cycle Engine with Serpentine 2-D Exhaust System Based on Infrared Stealth

Chen,

Wang,

Zhang

2023

Aerospace

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In the overall design process of the turbofan engine, it has become crucial to address the challenge of selecting design parameters that not only meet the flight thrust demand but also enhance engine economy. As the demand for stealth performance in future fighter aircraft increases, it becomes imperative to consider infrared stealth indicators during the design process. The adaptive cycle engine possesses an adjustable thermal cycle, necessitating careful attention to the selection of design parameters to fulfill the requirements. Therefore, this paper proposes a multi-objective optimization design method for the adaptive cycle engine that integrates infrared stealth technology. Initially, the parameter cycle model of the adaptive cycle engine is established based on the principles of aerodynamic and thermodynamic calculations. Subsequently, the model incorporates a serpentine two-dimensional (2-D) exhaust system to achieve infrared suppression. Meanwhile, a method for predicting the infrared characteristics is proposed to calculate the infrared radiation intensity of the engine exhaust system. Finally, the sequential quadratic programming algorithm is applied to comprehensively optimize the engine’s performance. The simulation results reveal that the multi-objective optimization design can effectively select appropriate design parameters to im-prove the engine, thereby reducing fuel consumption while meeting thrust requirements. This approach combines the consideration of infrared stealth technology with the optimization of engine performance, thus contributing to the development of advanced adaptive cycle engines.

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“…The static pressure on the upper and lower walls of the S-bend nozzle is very different from the axisymmetric nozzle. The flow near the wall will affects the static pressure, and the curved structure of the S-bend nozzle has a great influence on the state of the jet (Hui et al ,2021).…”

Section: Introductionmentioning

confidence: 99%

“…The nozzle outlet area is an important parameter, which has a great influence with the change of the vorticity of flow field (Abdelmotalib et al, 2021;Cheng et al, 2019Cheng et al, , 2017, while changing the center offset and the outlet area ratio has little effect on the aerodynamic performance of the nozzle (He et al, 2020).The static pressure on the upper and lower walls of the S-bend nozzle is very different from the axisymmetric nozzle. The flow near the wall will affects the static pressure, and the curved structure of the S-bend nozzle has a great influence on the state of the jet (Hui et al,2021).…”

Section: Introductionmentioning

confidence: 99%

Research on jet noise characteristics of aeroengine double S-bend nozzles with different cross sections

Shao

Zheng

et al. 2022

HFF

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Purpose This study aims to improve the survivability and maneuverability of the fighter,and study the stealth performance of fighter in the jet noise of aeroengine, it is of great significance to study the jet noise characteristics of double S-bend nozzles. Design/methodology/approach The multiparameter coupling and super-ellipse design methods are used to design the cross section of double S-bend nozzle. Taking unsteady flow information as the equivalent sound source, the noise signal at the far-field monitoring points were calculated with Ffowcs Williams–Hawkings (FW–H) method, and then, the sound source characteristics of the double S-bend nozzle are analyzed. Findings The results show that the internal flow of the S-bend nozzle with rectangular section is smoothed and the aerodynamic performance is better than super-ellipse section, the shear layer length of rectangular section is longer, the thickness is smaller and the mixing ability is stronger. The sound pressure level of the two S-bend nozzles decreases with the increase of the monitoring angle, and the sound pressure on the horizontal plane is greater than the vertical plane. In the direction of 40°–120°, the jet noise of rectangular nozzle is smaller, and the multiparameter coupled rectangular cross section structure is more applicable. Practical implications It is beneficial to reduce the jet noise of the engine tail nozzle and improve the stealth performance of the aircraft. Originality/value There is very little research on the jet noise characteristics of the double S-bend nozzle. The multiparameter coupling and the super-ellipse method are used to design the nozzle flow section to study the aerodynamic performance and jet noise characteristics of the double S-bend nozzle and to improve the acoustic stealth characteristics of the aircraft.

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Experimental investigation of serpentine nozzles for turbofan

Cited by 20 publications

References 23 publications

A Numerical Investigation of Film Cooling under the Effects of Different Adverse Pressure Gradients

A Numerical Investigation of Film Cooling under the Effects of Different Adverse Pressure Gradients

Multi-Objective Optimization Design of Adaptive Cycle Engine with Serpentine 2-D Exhaust System Based on Infrared Stealth

Research on jet noise characteristics of aeroengine double S-bend nozzles with different cross sections

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