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International Journal of Turbo & Jet-Engines最新文献

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Application of KH-RT model in lifting flame of methanol jet atomization KH-RT 模型在甲醇喷射雾化升腾火焰中的应用
International Journal of Turbo & Jet-Engines Pub Date : 2024-07-11 DOI: 10.1515/tjj-2024-0029
Qinyin Wang, Wenyan Song, Zhengxin Lai, Yu Fu
{"title":"Application of KH-RT model in lifting flame of methanol jet atomization","authors":"Qinyin Wang, Wenyan Song, Zhengxin Lai, Yu Fu","doi":"10.1515/tjj-2024-0029","DOIUrl":"https://doi.org/10.1515/tjj-2024-0029","url":null,"abstract":"\u0000 For the methanol jet atomization in a co-flow gas lifting flame, the self-developed WAVE model and KH-RT model were employed using the Saturne program to simulate the primary breakup of the jet column and the atomization of spray particles. Additionally, the unsteady flamelet model was utilized to simulate the combustion process. Comparing the calculated flame lifting height, droplet diameter distribution, and velocity distribution with experimental results demonstrates the atomization model’s ability to accurately capture the methanol fuel atomization process. This comparison verifies the reliability of both the atomization and combustion models, indicating their high accuracy. The study shows that upon injection from the nozzle, methanol fuel rapidly diffused, creating a cone-shaped spray structure. The high concentration of OH radicals is located close to the boundary between the regions of OH radical distribution and methanol distribution, gradually spreading downstream of the methanol jet. Furthermore, an increase in fuel flow rate resulted in a reduction in the flame’s lift height.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"50 3","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-07-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141655393","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Performance analysis of pulse detonation ramjet 脉冲引爆冲压式喷气机的性能分析
International Journal of Turbo & Jet-Engines Pub Date : 2024-05-24 DOI: 10.1515/tjj-2023-0084
Zhenkun Luo, Longxi Zheng, Jie Lu, Chenxu Peng, Zhiyi Xiao, Jiabo Zhang
{"title":"Performance analysis of pulse detonation ramjet","authors":"Zhenkun Luo, Longxi Zheng, Jie Lu, Chenxu Peng, Zhiyi Xiao, Jiabo Zhang","doi":"10.1515/tjj-2023-0084","DOIUrl":"https://doi.org/10.1515/tjj-2023-0084","url":null,"abstract":"\u0000 A Pulse Detonation Ramjet (PDR) performance evaluation model is established based on the component-based method. The influence law of working parameters of pulse detonation combustor (PDC), PDR geometry parameters, flight speed and altitude on the performance is analyzed. Results are as follows. (1) With the increase of the equivalent ratio, the PDR specific thrust first increases and then decreases, reaching a maximum value around 1.2, but the fuel specific impulse always decreases; (2) The change of inlet throat cross-sectional area has little effect on specific thrust and fuel specific impulse, but the increase of nozzle throat cross-sectional area will have a negative effect; (3) PDR specific thrust and fuel specific impulse increase first and then decrease with the increase of flight Mach number and altitude; (4) Compared with a ramjet engine, the advantage range of PDR can reach 18.04 %, but gradually decreases with the increase of Mach number.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"3 10","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141099079","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Performance analysis of a gas turbine engine with intercooling and regeneration process - Part 1 带中间冷却和再生过程的燃气涡轮发动机性能分析 - 第 1 部分
International Journal of Turbo & Jet-Engines Pub Date : 2024-05-16 DOI: 10.1515/tjj-2023-0095
Jaimon D. Quadros, Prashanth Thalambeti, Mamadou Ndiaye, Yakub I. Mogul
{"title":"Performance analysis of a gas turbine engine with intercooling and regeneration process - Part 1","authors":"Jaimon D. Quadros, Prashanth Thalambeti, Mamadou Ndiaye, Yakub I. Mogul","doi":"10.1515/tjj-2023-0095","DOIUrl":"https://doi.org/10.1515/tjj-2023-0095","url":null,"abstract":"\u0000 Auxiliary systems, such as regeneration and intercooling, have been integrated with the primary gas generator to improve power production and fuel economy in modern gas turbine power plants. Implementing these techniques in turbine engines is challenging due to size, weight, and complex flow patterns. A solution is to use a turboprop engine with a smaller mass flow rate and simpler gas paths. The current study involves the numerical analysis of performance parameters namely, specific power (SP), thermal efficiency (η), and enthalpy based specific fuel consumption (EBSFC) of a turboprop engine using thermodynamic parameters namely, pressure ratio (PR), nozzle pressure ratio (NPR), turbine inlet temperature (TIT), regeneration efficiency (R), and intercooling efficiency (E). The results prove that the introduction of regeneration and intercooling showed significant improvement in the power developed, and reduced fuel consumption.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"38 16","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140971436","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Predicting compressor mass flow rate using various machine learning approaches 使用各种机器学习方法预测压缩机质量流量
International Journal of Turbo & Jet-Engines Pub Date : 2024-05-07 DOI: 10.1515/tjj-2023-0105
I. Yazar, Yildiray Anagun, Ş. Işık
{"title":"Predicting compressor mass flow rate using various machine learning approaches","authors":"I. Yazar, Yildiray Anagun, Ş. Işık","doi":"10.1515/tjj-2023-0105","DOIUrl":"https://doi.org/10.1515/tjj-2023-0105","url":null,"abstract":"\u0000 A major focus of the present study is to construct high-fidelity models for predicting corrected mass flow rates based on the collected compressor map data. Both traditional machine learning research and modern deep learning techniques have been employed to obtain well-fitted regression models of compressor mass flow rate. As traditional machine learning methods, Multiple Linear Regression and Random Forest, are conducted on compressor maps for prediction of corrected mass flow rate. The time series-based deep learning models are able to capture the overall trend of a given input for specific map data. Therefore, a time series-based deep learning technique, namely Gated Recurrent Unit has been employed to improve regression results. Besides, the prediction capabilities of the models, results also show that the proposed models can be used for the development of dynamic aero-thermal mathematical models of gas turbine engines and mass flow rate models created for dynamic compressors in other disciplines.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"69 s283","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141002297","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators 利用微型涡流发生器对 RBCC 入口的扰流喷射模式进行计算分析
International Journal of Turbo & Jet-Engines Pub Date : 2024-05-03 DOI: 10.1515/tjj-2024-0015
Ritul Raj, Ganapati N. Joshi, Sunil Chandel, Ranjan Kumar Mishra
{"title":"Computational analysis of the scramjet mode of the RBCC inlet using micro vortex generators","authors":"Ritul Raj, Ganapati N. Joshi, Sunil Chandel, Ranjan Kumar Mishra","doi":"10.1515/tjj-2024-0015","DOIUrl":"https://doi.org/10.1515/tjj-2024-0015","url":null,"abstract":"\u0000 A computational study of a three ramped dual duct Rocket Based Combined Cycle (RBCC) engine inlet at scramjet mode using different types of MVG (micro vortex generator) arrays were conducted. The definite geometry of engine inlet was operated at hypersonic speeds of Mach 5 and 7 to study the effect of the arrays of delta ramp (DR), rectangular vane (RRV) and ramp vane (RV) on the pressure recovery, exit Mach number, the mass flow rate and Shock wave Boundary Layer interaction (SWBLI). The study was performed considering same heights for all the configurations of MVG array and were positioned at the point of shock impingement on the ramp which caused the separation bubble. The computational analysis was done using k-omega model in Fluent Workbench of Ansys.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"106 S6","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-05-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141016185","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Effect of asymmetric leading edge on transition of suction side 不对称前缘对吸气侧过渡的影响
International Journal of Turbo & Jet-Engines Pub Date : 2024-04-22 DOI: 10.1515/tjj-2023-0035
Yutian Chen, Qun Zheng, Zhijie Li, Bin Jiang
{"title":"Effect of asymmetric leading edge on transition of suction side","authors":"Yutian Chen, Qun Zheng, Zhijie Li, Bin Jiang","doi":"10.1515/tjj-2023-0035","DOIUrl":"https://doi.org/10.1515/tjj-2023-0035","url":null,"abstract":"\u0000 Asymmetric leading edge offers several advantages over conventional leading edge. However, there are few related published research on compressor blades. This study proposes a blade parameterization method that superimposing the thickness distribution on the camber line at the middle and curve fitting at the leading and trailing edges. This parameterization method is applied to a stator in the final stage of an axial compressor, and numerical simulation is used to calculate the aerodynamic performance at various attack angles under the designed inlet Mach number. There is an optimal deflection angle regardless of which side of the leading edge deflects, and deflection toward the pressure side is conducive to the suppression of separation bubble near the leading edge at positive attack angle. When the maximum curvature of the pressure side is decreased, the operating range changed slightly, but the positive attack angle range grew from 5.166° to 5.466°.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"16 20","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140672305","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2 通过中冷和再生对燃气涡轮发动机进行性能分析--第 2 部分
International Journal of Turbo & Jet-Engines Pub Date : 2024-04-16 DOI: 10.1515/tjj-2023-0096
Suhas Poojary, J. Quadros, Prashanth Thalambeti, Hanumanthraya Rangaswamy, Ma Mohin
{"title":"Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2","authors":"Suhas Poojary, J. Quadros, Prashanth Thalambeti, Hanumanthraya Rangaswamy, Ma Mohin","doi":"10.1515/tjj-2023-0096","DOIUrl":"https://doi.org/10.1515/tjj-2023-0096","url":null,"abstract":"\u0000 The current study aims to amplify the predictive ability of the numerical model developed for a gas turbine engine-based power plants by process of regeneration and intercooling. Artificial neural networks (ANN) and adaptive neuro-fuzzy interface systems (ANFIS) are the two techniques mainly concentrated in this study which were not properly implemented previously. The performance parameters namely, specific power (SP), thermal efficiency (η), and enthalpy based specific fuel consumption (EBSFC) of a Turboprop engine were predicted using thermodynamic parameters namely, pressure ratio (PR), nozzle pressure ratio (NPR), turbine inlet temperature (TIT), for constant regeneration (R), and intercooling (E) efficiencies. The results showed that a high regression result R\u0000 \u0000 2\u0000 of 0.9831 and 0.9899 was found for the ANFIS model for η for training and testing, respectively. Also, the ANFIS model resulted in best performance of the performance characteristics when compared to ANN.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"350 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140698308","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes 排气压力对带有吸气孔的跨音速压缩机定子中冲击波/边界层相互作用的影响
International Journal of Turbo & Jet-Engines Pub Date : 2024-04-16 DOI: 10.1515/tjj-2022-0059
Bai Li, Xun Zhou, Lei Luo, Wei Du
{"title":"Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes","authors":"Bai Li, Xun Zhou, Lei Luo, Wei Du","doi":"10.1515/tjj-2022-0059","DOIUrl":"https://doi.org/10.1515/tjj-2022-0059","url":null,"abstract":"\u0000 This paper numerically investigated the influence of bleed pressure on the shock-wave/boundary-layer interaction in a transonic compressor stator with a row of suction holes. These suction holes are arranged on the suction surface in the spanwise direction. Six different bleed pressure ratios are studied at an inlet Mach number of 1.0. Results show that the reduction in the pressure loss increases as the bleed pressure decreases, and the maximum relative decline is 36.4 % when the flow loss caused by the suction flow path is taken into account. The bleeding of suction holes changes the shock wave structure, and the modified shock wave structure is three-dimensional. As the bleed pressure decreases, the tangential momentum of boundary layer increases. A strong spanwise variation in the boundary layer is observed downstream of the suction hole. Turning the flow direction and creating a favorable pressure gradient are key reasons for controlling boundary layer separation.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"73 3","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140695430","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Research on an optimization design method for a TBCC propulsion scheme TBCC 推进方案的优化设计方法研究
International Journal of Turbo & Jet-Engines Pub Date : 2024-04-05 DOI: 10.1515/tjj-2023-0085
Pinxin Wu, Wenyan Song, Dongqing Zhang
{"title":"Research on an optimization design method for a TBCC propulsion scheme","authors":"Pinxin Wu, Wenyan Song, Dongqing Zhang","doi":"10.1515/tjj-2023-0085","DOIUrl":"https://doi.org/10.1515/tjj-2023-0085","url":null,"abstract":"\u0000 An optimization methodology for a TBCC propulsion schemes was established for hypersonic vehicles, focusing on the integration of aircraft and engine performance. Altitude-velocity characteristics of TBCC propulsion were obtained through engine performance calculations. By analyzing mission requirements, lift-drag characteristics, and flight constraints, the take-off thrust-weight ratio and wing load of the vehicle were optimized to meet the flight conditions. In addition, the fuel ratio was calculated. To determine the vehicle’s gross take-off weight and the engine’s take-off thrust, a model considering the weight of the vehicle and the turbine engine were used. The optimization process selects four thermodynamic cycle parameters for the turbine engine as the independent variables. An improved particle swarm optimization-back propagation neural network was used to establish the relationship between the four parameters and the gross take-off weight, aiming to minimize the vehicle’s weight. The results of the optimization process show that the total take-off weight of the optimized vehicle has decreased from 112363.41 kg to 102218.98 kg. The required uninstalled take-off thrust of TBCC has also been reduced from 162.86 kN to 147.49 kN, resulting in a decrease in mass flow from 156.50 kg/s to 133.30 kg/s.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"5 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140737563","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
Design and analysis of air intake of subsonic cruise vehicle with experimental validation 亚音速巡航飞行器进气口的设计与分析及实验验证
International Journal of Turbo & Jet-Engines Pub Date : 2024-04-04 DOI: 10.1515/tjj-2024-0007
Yogesh T. V., Laasya Priya Nidamarty, Ramanamurthy S. V., S. K. Panigrahi
{"title":"Design and analysis of air intake of subsonic cruise vehicle with experimental validation","authors":"Yogesh T. V., Laasya Priya Nidamarty, Ramanamurthy S. V., S. K. Panigrahi","doi":"10.1515/tjj-2024-0007","DOIUrl":"https://doi.org/10.1515/tjj-2024-0007","url":null,"abstract":"\u0000 A Subsonic Cruise Vehicle (SCV) is designed with a Submerged Air intake with appreciable total pressure recovery along with acceptable distortion levels. A steady, 3D, density based, one equation turbulence model in congregation with Navier Stokes is used to simulate the flow field in commercial CFD code. In the initial iteration of the intake, the numerical simulation pointed towards a large scope in the improvement of the geometry. Subsequently, the design changes have been successfully incorporated and analyzed. The performance of these modified intakes was evaluated by measuring distortion coefficient and total pressure recovery. An experimental validation case has been demonstrated in a subsonic wind tunnel, which proves the close match with the CFD prediction. The comparison between the performances of the intakes has been made. The redesigned submerged air intake is flown successfully with SCV at all flight conditions within the acceptable distortion limits.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"54 11","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-04-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140742942","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
引用次数: 0
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