Aerospace Science and Technology最新文献_第7页

Multi-fidelity simulation of inlet mode transition with smooth thrust of turbine based combined cycle 多保真模拟涡轮机联合循环平滑推力的进气模式转换

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-11-01 DOI: 10.1016/j.ast.2024.109710

Jun Liu , Jinsheng Zhang , Zhengxu Hua , Keyu Zhou , Huacheng Yuan

{"title":"Multi-fidelity simulation of inlet mode transition with smooth thrust of turbine based combined cycle","authors":"Jun Liu , Jinsheng Zhang , Zhengxu Hua , Keyu Zhou , Huacheng Yuan","doi":"10.1016/j.ast.2024.109710","DOIUrl":"10.1016/j.ast.2024.109710","url":null,"abstract":"<div><div>A multi-fidelity simulation method of external and internal flow has been developed using commercial software to achieve a smooth thrust of the turbine-based combined-cycle (TBCC) propulsion system. This platform enables the investigation of the flow field and performance of the TBCC propulsion system at different mode transition schemes. The integrated multi-fidelity simulation includes the inlet, turbojet engine, ramjet engine, and nozzle, providing insights into the operation process of the TBCC propulsion system during the transition from turbojet mode to ramjet mode. Three mode transition schemes are proposed: critical mode transition, constant aerodynamic interface plane (AIP) Mach number mode transition, and linear mode transition. From the perspective of TBCC inlet, the performance of the critical mode transition exhibits the best performance among these mode transition schemes, while the linear mode transition performs the worst. However, from the viewpoint of the TBCC propulsion system and the hypersonic vehicle, the performance of constant AIP Mach number mode transition is the best. The non-dimensional thrust increases almost linear from 1.0 to 1.2, enabling hypersonic vehicle to accelerate steadily during the transition from turbojet mode to ramjet mode.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109710"},"PeriodicalIF":5.0,"publicationDate":"2024-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142664222","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Study on concentration distribution and detonation characteristics of typical multiphase fuel in orthogonal flow field 正交流场中典型多相燃料的浓度分布和爆炸特性研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-31 DOI: 10.1016/j.ast.2024.109704

Linghui Zeng , Zhongqi Wang , Jianping Li , Xing Chen

{"title":"Study on concentration distribution and detonation characteristics of typical multiphase fuel in orthogonal flow field","authors":"Linghui Zeng , Zhongqi Wang , Jianping Li , Xing Chen","doi":"10.1016/j.ast.2024.109704","DOIUrl":"10.1016/j.ast.2024.109704","url":null,"abstract":"<div><div>The fuel concentration distribution and detonation characteristics are important for performance evaluation. In order to meet the needs of airdrop, launcher and missile, the transient flow and detonation process of multiphase fuel in orthogonal flow field are analyzed by experiments and numerical simulations. The dynamic detonation model of ethyl ether (EE), propylene oxide (PO) and tetrahydro dicyclopentadiene (JP-10) is built. The flow process, concentration distribution, overpressure, temperature and detonation wave structure of the three fuels are obtained. The results show that the falling velocity has obvious influence on the detonation process of fuel droplets. The falling velocity of 0.5 Ma makes the fuel concentration distribution more uniform and the energy output is better. The peak overpressure of EE, PO and JP-10 is 2.88 MPa, 3.21 MPa and 2.96 MPa respectively. The peak temperature is 2885 K, 3230 K and 2955 K respectively. The burn out rate increases by 8.5%, 8.1% and 13.7% respectively. JP-10 has higher sensitivity to falling velocity, and there are obvious secondary peaks of overpressure in low-speed state. PO has higher stability for falling velocity, and the scaled length of high temperature/pressure after detonation wave is 0.145 m·kg<sup>-1/3</sup>.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109704"},"PeriodicalIF":5.0,"publicationDate":"2024-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142592546","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Experimental and numerical investigations into cold flow characteristics of multiple micro-mixing jets for hydrogen-rich gas turbines 富氢燃气轮机多重微混合喷流冷流特性的实验和数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-31 DOI: 10.1016/j.ast.2024.109702

Xuanren Chen , Hui Wang , Xiangyu Wang , Ning Wang , Xiang Liu , Dehuang Huang

{"title":"Experimental and numerical investigations into cold flow characteristics of multiple micro-mixing jets for hydrogen-rich gas turbines","authors":"Xuanren Chen , Hui Wang , Xiangyu Wang , Ning Wang , Xiang Liu , Dehuang Huang","doi":"10.1016/j.ast.2024.109702","DOIUrl":"10.1016/j.ast.2024.109702","url":null,"abstract":"<div><div>To explore the flow field of micro-mixing jets, cold flow characteristics of a model Micromix burner were investigated by particle image velocimetry (PIV) system and Large-eddy simulation (LES) model. Results show that LES results are in good agreement with experimental results. In the flow field of multiple micro-mixing jets, the jet velocities of nozzles farther away from the burner center have a high increase and decay rate. When the outlet Reynolds number increases, the Reynolds stress increases first and then decreases in the merging region indicating that the velocity fluctuation disappears in the second jet half, but it has little effect on the flow field structure. Comparing the flow fields of round multiple micro-mixing jets, the merging point and combined point in the elliptical jets flow field move backward. Moreover, the maximum velocity for elliptical jets is also faster than the round jets, which is caused by the high turbulent kinetic energy in the elliptical jet flow field. When the tube spacing increases from 2 to 3 times the tube diameter, positions of the two feature points change linearly. Further, the surrounding jets can decrease the velocity attenuation of the center nozzle and elongate the axial length of the two feature regions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109702"},"PeriodicalIF":5.0,"publicationDate":"2024-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142592545","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Prediction of pressure distribution and aerodynamic coefficients for a variable-sweep wing 预测变掠翼的压力分布和空气动力系数

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-31 DOI: 10.1016/j.ast.2024.109706

Yuqi Lei , Xiaomin An , Yihua Pan , Yue Zhou , Qi Chen

{"title":"Prediction of pressure distribution and aerodynamic coefficients for a variable-sweep wing","authors":"Yuqi Lei , Xiaomin An , Yihua Pan , Yue Zhou , Qi Chen","doi":"10.1016/j.ast.2024.109706","DOIUrl":"10.1016/j.ast.2024.109706","url":null,"abstract":"<div><div>To satisfy the performance requirements across multiple speed ranges, a variable-sweep wing (sweep angle range from 25° to 40°) is derived from the BQM-34 “Firebee” drone model. However, predicting aerodynamic characteristics across various flight conditions and sweep angles is a challenging task. Traditional methods like CFD and wind tunnel testing are both time consuming and expensive. In order to efficiently predict the pressure distributions and aerodynamic coefficients, a novel network that combines a Radial Basis Function Network (RBFN) and a Convolutional Auto-Encoder (CAE) is proposed. Two distinct loss function methods, the standard Pressure-Targeted Method (PTM) and the newly developed Comprehensive Evaluation Method (CEM), are employed to optimize the network's predictive performance. These methods are evaluated on datasets with both trained and untrained sweep angles. The results show that while both PTM and CEM accurately predict pressure distributions, the enhanced CEM provides more uniform and reliable predictions. Moreover, the CEM method significantly outperforms PTM in predicting aerodynamic coefficients, reducing errors by over 50%. The proposed RBFN-CAE network with the CEM loss function offers an effective way to predict the aerodynamic characteristics of a variable-sweep wing, improving predictive models in aerodynamic applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109706"},"PeriodicalIF":5.0,"publicationDate":"2024-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142586304","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Experimental study on loss and flow mechanism of variable stator vanes in high-pressure compressor with bleed 带排气的高压压缩机中可变定子叶片的损耗和流动机理的实验研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-31 DOI: 10.1016/j.ast.2024.109686

Chen Xu, Shaowen Chen, Zehao Li

{"title":"Experimental study on loss and flow mechanism of variable stator vanes in high-pressure compressor with bleed","authors":"Chen Xu, Shaowen Chen, Zehao Li","doi":"10.1016/j.ast.2024.109686","DOIUrl":"10.1016/j.ast.2024.109686","url":null,"abstract":"<div><div>In modern compressors, variable stator vanes are increasingly utilized. These vanes require a specific gap between their leading and trailing edges and the casing/hub to prevent contact during rotation. For multi-stage axial compressors employing variable stator vanes, understanding the impact of clearance variations on compressor performance is crucial during design. This study focuses on experimental research conducted on a high-pressure compressor equipped with variable stator vanes and bleed, using a real engine structure. The investigation delves into the loss characteristics and flow mechanisms within the variable mechanism's flow field. Results show that, with the identical penny diameter, increasing radial clearance initially decreases flow field loss, but then loss rises, reaching a minimum with a 2 mm (1.25% blade height) clearance. Conversely, with the same radial clearance, increasing penny diameter initially increases loss, which then decreases, with larger penny diameters resulting in smaller losses. Based on these findings, it can be inferred that a clearance of around 2 mm substantially reduces losses within the vane. Losses within 0–10% of the blade height from the endwall mainly stem from penny leakage vortex and their interaction with passage vortex, while losses within 10–20% of the blade height primarily arise from passage vortex, thus mitigating overall losses. The study demonstrates that, compared to zero-clearance vanes, variable stator vanes with a partial gap resulted in lower total pressure losses and better flow field control.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109686"},"PeriodicalIF":5.0,"publicationDate":"2024-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552909","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Fast aerodynamic analysis method for three-dimensional morphing wings based on deep learning 基于深度学习的三维变形机翼快速气动分析方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-29 DOI: 10.1016/j.ast.2024.109690

Ruolong Xie , Zhiqiang Wan , De Yan , Wenwei Qiu

引用次数: 0

Closed-loop AI-aided image-based GNC for autonomous inspection of uncooperative space objects 基于图像的闭环人工智能辅助 GNC，用于自主检测不合作的空间物体

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-29 DOI: 10.1016/j.ast.2024.109700

Andrea Brandonisio , Michele Bechini , Gaia Letizia Civardi, Lorenzo Capra, Michèle Lavagna

引用次数: 0

Numerical study of aluminum combustion with agglomerate size distribution in solid rocket motor 固体火箭发动机中带有结块粒度分布的铝燃烧数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109696

He Chen , Wenjing Yang , Qingyun Sheng , Huangpeng Wang , Yan Ba , Peijin Liu , Wen Ao

{"title":"Numerical study of aluminum combustion with agglomerate size distribution in solid rocket motor","authors":"He Chen , Wenjing Yang , Qingyun Sheng , Huangpeng Wang , Yan Ba , Peijin Liu , Wen Ao","doi":"10.1016/j.ast.2024.109696","DOIUrl":"10.1016/j.ast.2024.109696","url":null,"abstract":"<div><div>The aluminum agglomerate size distribution plays an important role in influencing the particle distributed combustion in motor, which subsequently affects the performance of solid rocket motor significantly. In this work, a three-phase model to describe distributed combustion of aluminum agglomerates is established based on the Eulerian-Lagrangian method. Then, the agglomerate size, including mono size and distributed size, is studied to reveal its effect on aluminum combustion and motor flow field. The simulated results indicate that the increasing agglomerate mono size observes the obvious decrease of the average temperature inside the motor combustion chamber, implying the low combustion efficiency of large agglomerate size. When considering the agglomerate size distribution, the size distribution mode and the mean size <em>D</em><sub>43</sub> determine the combustion efficiency together. In particular, even the mean size is similar, with different distribution mode, like skewed distribution, bimodal or trimodal distribution, the combustion efficiency and flow field parameters are nonnegligible different. However, when the size distribution mode is the same and the peak range is similar, the mean size <em>D</em><sub>43</sub> becomes the only and predominant factor as the mono size.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109696"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571523","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Experimental and numerical study on the mechanism of leakage flow influence on the performance of high-speed diffuser cascade 泄漏流对高速扩散器级联性能影响机理的实验和数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109698

Tianshuo Huang , Xiaozhi Kong , Huawei Lu , Zhengyang Dong , Pengwei Fan

{"title":"Experimental and numerical study on the mechanism of leakage flow influence on the performance of high-speed diffuser cascade","authors":"Tianshuo Huang , Xiaozhi Kong , Huawei Lu , Zhengyang Dong , Pengwei Fan","doi":"10.1016/j.ast.2024.109698","DOIUrl":"10.1016/j.ast.2024.109698","url":null,"abstract":"<div><div>For the purpose of further enhancing the performance of the cascade, this study takes the high-load diffuser cascade as the research object. By simplifying the design of the cascade with leakage flow in experiments, tests and numerical simulation were conducted at design incidence angle of 0° and the minimum loss incidence angle of -4° for different leakage flow rates and leakage inflow angles. The results show that changes in leakage flow rates and inflow angles will lead to variations in the momentum thickness of the boundary layer at the leading edge of the cascade, thereby affecting the cascade performance. Increasing the leakage flow rate results in an increase in the spanwise and tangential momentum of the leakage flow, a thickening in the axial momentum thickness of the boundary layer at the cascade leading edge, a reduction in the static pressure on the endwall within the cascade passage, a decrease in the expansion capability, and a raising in losses. Increasing the leakage inflow angle results in no change in the spanwise momentum of the leakage flow, an increase in the tangential momentum, a thickening in the tangential momentum thickness of the boundary layer at the cascade leading edge, a gradual increase in the static pressure at the leading edge, but a decrease in the static pressure within the cascade passage, leading to a decrease in the expansion capability. Changes in the tangential momentum of the leakage flow mainly affect the passage vortex, the trailing shedding vortex and the concentrated shedding vortex within the cascade passage.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109698"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142560591","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Numerical study on the combustion characteristics and performances of single and multi-injectors in a scramjet combustor 关于争气式喷气燃烧器中单喷射器和多喷射器的燃烧特性和性能的数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109697

Seung-Min Jeong , Jae-Eun Kim , Min-Su Kim , Bu-Kyeng Sung , Jeong-Yeol Choi , Kenneth H. Yu

{"title":"Numerical study on the combustion characteristics and performances of single and multi-injectors in a scramjet combustor","authors":"Seung-Min Jeong , Jae-Eun Kim , Min-Su Kim , Bu-Kyeng Sung , Jeong-Yeol Choi , Kenneth H. Yu","doi":"10.1016/j.ast.2024.109697","DOIUrl":"10.1016/j.ast.2024.109697","url":null,"abstract":"<div><div>The present study numerically investigates the combustion characteristics and performance of a direct-connect gaseous hydrogen-fueled scramjet combustor depending on the injector scheme. A comprehensive numerical simulation was conducted with an improved delayed detached eddy simulation (IDDES) approach. The framework utilized a high-order accurate numerical scheme to ensure the high fidelity of the results. A total of ten cases were considered combining two injector schemes and five injection pressure conditions. Each injector scheme had a similar range of global equivalence ratios. Numerical results revealed the differences in the local dynamics of the counter-rotating vortex pair. The multi-injector case did not maintain the jet's systemic vortex structure, which plays a primary role in the fuel-air mixing and burning. It owes to the interactions between the jet-jet and the jet-wall surface, where the interaction leads to the loss of momentum. This characteristic of the multi-injector makes the fuel-air mixing contact surface get closer to a thin-flat layer, resulting in the flame being anchored on a flat shear layer over the entire combustor. As a result, the combustion efficiency of the multi-injector is much lower than that of the single injector under a similar equivalence ratio range. Present results indicate that the multi-injector, which is expected to increase the combustion performance by maximizing the fuel-air contact surface, may operate in contrast to its original anticipation under certain configurations and conditions. It also suggests that optimizing the combustion performance requires careful design of injector distributions considering the distances and interactions between injector-to-injector and injector-to-wall.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109697"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142662557","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0