Hot Streak Characterization of High-Performance Double-Serpentine Exhaust Nozzles at Design Conditions

Crowe, Darrell S.; Martin, Christopher L.

doi:10.2514/1.b37235

Cited by 12 publications

(2 citation statements)

References 18 publications

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“…The demand for increasingly higher performance has led to an increase in the temperature at the inlet of turbines in the design of modern aero-engines. This, in turn, increases the thermal load on serpentine nozzles and causes problems such as local hot streaks [1,2]. Film cooling technology has good cooling effects and has attracted the attention of many scholars [3,4].…”

Section: Introductionmentioning

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: Introductionmentioning

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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“…This effect becomes particularly prominent in the instance of double serpentine nozzles, where regions with high temperature, often termed as hot streaks, tend to develop along the nozzle surface. These high-temperature zones will cause material degradation of the nozzle and adversely affect the IR stealth capabilities of the nozzle [17,18].…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective Bayesian Optimization Design of Elliptical Double Serpentine Nozzle

Zhang,

Yang,

Wang

et al. 2023

Aerospace

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The use of traditional optimization methods in engineering design problems, specifically in aerodynamic and infrared stealth optimization for engine nozzles, requires a large number of objective function evaluations, therefore introducing a considerable challenge in terms of time constraints. In this paper, this limitation is addressed by using a sample-efficient multi-objective Bayesian optimization that takes Kriging as a surrogate model and Expected Hypervolume Improvement as the infill criterion. Using this approach, the probabilistic model is continuously established and updated, and the approximate Pareto front is obtained at a relatively small computational budget. The objective of this work is to evaluate the applicability of employing a multi-objective Bayesian optimization framework for the aerodynamic-infrared shape optimization of an elliptical double serpentine nozzle at 6 km flight condition, where the objective functions are evaluated by means of high-fidelity computational fluid dynamics and reversed Monte Carlo ray tracing simulations. We achieve good results in both infrared radiation signature reduction and aerodynamic performance improvement with a reasonable number of evaluations, indicating that the proposed method is effective and efficient for tackling the computationally intensive optimization challenges in the aircraft design.

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Experimental investigation on the effects of complex pressure gradients on the film cooling effectiveness of a serpentine nozzle

Hui,

Shi,

Zhou

et al. 2024

Applied Thermal Engineering

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Hot Streak Characterization of High-Performance Double-Serpentine Exhaust Nozzles at Design Conditions

Cited by 12 publications

References 18 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 Bayesian Optimization Design of Elliptical Double Serpentine Nozzle

Experimental investigation on the effects of complex pressure gradients on the film cooling effectiveness of a serpentine nozzle

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