Design and optimization of aerospike nozzle for rotating detonation engine

Liu, Xiang Yang; Cheng, Miao; Yunzhen, Zhang

doi:10.1016/j.ast.2021.107300

Cited by 34 publications

(3 citation statements)

References 46 publications

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“…The rate of flow, speed, direction, mass, form, and/or pressure of the stream that emerges from nozzles are commonly controlled. The purpose of the rocket nozzle is to efficiently transform the propellant's thermal energy into kinetic energy so that high exhaust velocity can be achieved in the intended direction [7]. The three primary components of a rocket nozzle are the throat, the divergent section, and the convergent section [6].…”

Section: Nozzle Concepts Thrust and Performancementioning

confidence: 99%

Development and Numerical validation of an Aerospike nozzle Contour Design

Sampathkumar,

Mayekar

et al. 2024

MATEC Web Conf.

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Aerospike nozzle simplified design and analysis, as well as test results, are presented. New techniques in nozzle design have been used to improve the performance of current rocket engines. The use of an aerospike nozzle is one such technique. It outperforms the existing proven bell nozzle in terms of overall performance. This study analyses the development and flow analysis of an aerospike nozzle at sea level, validating their results by taking into account currently used bell nozzles. The flow over the aerospike pump is investigated in higher depth using computational fluid dynamics under an autonomous fire testing condition. This test showed that the approximate design method used to determine an aerospike nozzle shape can lead to extremely effective nozzles. A model of the current 7.45 kN bell nozzle was selected as a specimen to develop an aerospike Nozzle. Gambit and Fluent software were used to model and examine the flow characteristics of building the aerospike nozzle. The developed aerospike nozzle shows a nearly 2% increase in performance over the existing nozzle.

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Section: Nozzle Concepts Thrust and Performancementioning

confidence: 99%

Development and Numerical validation of an Aerospike nozzle Contour Design

Sampathkumar,

Mayekar

et al. 2024

MATEC Web Conf.

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“…Numerous works have highlighted the significance of nozzles concerning the flow analyses (see for instance [1,2,3]), the jet noise source and acoustics (see for instance [4,5,6,7,8]), the nozzle materials [9,10,11], the nozzle vibrations [12], the fluid-structure interactions and vibroacoustics [13,14,15,16], the nozzle optimization [17,18,19,20,21,22]. The effects of uncertainties in nozzle models have also been studied, see for instance [23,24,25,26].…”

Section: Introductionmentioning

confidence: 99%

Updating Nonlinear Stochastic Dynamics of an Uncertain Nozzle Model Using Probabilistic Learning With Partial Observability and Incomplete Dataset

Capiez-Lernout,

Ezvan,

Soize

2024

Journal of Computing and Information Science in Engineering

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This paper introduces a methodology for updating the nonlinear stochastic dynamics of a nozzle with uncertain computational model. The approach focuses on a high-dimensional nonlinear computational model constrained by a small target dataset. Challenges include the large number of degrees-of-freedom, geometric nonlinearities, material uncertainties, stochastic external loads, under-observability, and high computational costs. A detailed dynamic analysis of the nozzle is presented. An updated statistical surrogate model relating the observations of interest to the control parameters is constructed. Despite small training and target datasets, and partial observability, the study successfully applies Probabilistic Learning on Manifolds (PLoM) to address these challenges. PLoM captures geometric nonlinear effects and uncertainty propagation, improving conditional mean statistics compared to training data. The conditional confidence region demonstrates the ability of the methodology to accurately represent both observed and unobserved output variables, contributing to advancements in modeling complex systems.

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“…They found that the re-initiation phenomenon is related to the injection pressure of the propellant. Furthermore, some studies have explored the impact of factors, such as total pressure [16], thrust efficiency [17], nozzle design [18][19][20], and tail nozzle characteristics [21,22]. Owing to the ignition challenges associated with large-molecule fuels, Zhang [23] utilized the addition of hydrogen to facilitate auxiliary detonation.…”

Section: Introductionmentioning

confidence: 99%

Effects of Ozone Addition on Multi-Wave Modes of Hydrogen–Air Rotating Detonations

2023

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Ozone addition presents a promising approach for optimizing and regulating both combustion and ignition mechanisms. In Rotating Detonation Engines (RDEs), investigating the impact of ozone addition is particularly important due to the fact of their unique operating conditions and potential for improved efficiency. This study explores the influence of ozone concentration, total temperature, and equivalent ratio on the combustion characteristics of a hydrogen–air mixture infused with ozone. Utilizing the mixture as a propellant, the combustion chamber of a continuous rotating detonation engine is replicated through an array of injection ports, with numerical simulations conducted to analyze the detonation wave combustion mode. Our results show that an increase in total temperature leads to an increase in the number of detonation waves. Incorporating a minor quantity of ozone can facilitate the ignition process for the detonation wave. Increasing the ozone content can result in the conversion from a single-wave to dual-wave or multi-wave mode, providing a more stable combustion interface. A low ozone concentration acts as an auxiliary ignition agent and can significantly shorten the induction time. As the total temperature increases, the detonation propagation velocity and the peak heat release rate both decrease concurrently, which leads to a decline in the exit total pressure and an augmentation in the specific impulse. Employing ozone exerts a minimal impact on the detonation propagation and the overall propulsion performance. The requirement for ozone-assisted initiation differs noticeably between rich and lean combustion.

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Design and optimization of aerospike nozzle for rotating detonation engine

Cited by 34 publications

References 46 publications

Development and Numerical validation of an Aerospike nozzle Contour Design

Development and Numerical validation of an Aerospike nozzle Contour Design

Updating Nonlinear Stochastic Dynamics of an Uncertain Nozzle Model Using Probabilistic Learning With Partial Observability and Incomplete Dataset

Effects of Ozone Addition on Multi-Wave Modes of Hydrogen–Air Rotating Detonations

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