International Journal of Turbo & Jet-Engines最新文献

The International Journal of Turbo and Jet Engines 涡轮和喷气发动机国际期刊

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-12-25 DOI: 10.1515/tjj-2023-0101

Valery Sherbaum

引用次数: 0

Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine 变速涡轮轴发动机高带宽线性主动干扰抑制控制方法研究

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-12-19 DOI: 10.1515/tjj-2023-0090

Bo Huang, Wenbo Li, Yerong Peng, Jie Song

引用次数: 0

Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine 镁粉燃料水冲压喷气发动机进气道结构对燃烧流结构的影响

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-12-12 DOI: 10.1515/tjj-2023-0080

Wei Xu, Zhi-Long Yang, Yunkai Wu, Guo-Yu Ding, Rui Xue, Jun-Li Liu, Hai-Jun Sun

{"title":"Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine","authors":"Wei Xu, Zhi-Long Yang, Yunkai Wu, Guo-Yu Ding, Rui Xue, Jun-Li Liu, Hai-Jun Sun","doi":"10.1515/tjj-2023-0080","DOIUrl":"https://doi.org/10.1515/tjj-2023-0080","url":null,"abstract":"Abstract Different inlet structures have a significant impact on the internal flow characteristics of a solid-magnesium powder water ramjet engine. Based on the magnesium-water reaction model, a computational fluid dynamics (CFD) method is applied to establish a numerical simulation method for the internal flow field of the engine, and the internal flow characteristics of the engine under different inlet structure conditions are studied. The simulation results show that high-temperature gas can effectively promote the ignition of magnesium powder at the top of the combustion chamber, while accelerating the evaporation of the first inlet water and increasing the combustion rate of magnesium powder. The secondary inlet has the most significant effect on the temperature inside the combustion chamber. When the secondary inlet flow rate increases towards the top of the combustion chamber, it increases the amount of heat absorbed by the evaporating water at the top of the chamber, thereby reducing the temperature at the top of the combustion chamber. However, when the flow rate is low, it results in insufficient oxidizer at the top of the combustion chamber, which is unfavorable for the combustion of magnesium powder.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"27 11","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-12-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138632933","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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

C conjugate heat transfer simulation of swirl internal cooling on blade leading edge 叶片前缘漩涡内冷却的 C 共轭传热模拟

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-11-29 DOI: 10.1515/tjj-2023-0051

Yuting Jiang, Haosu Zhang, Kang Huang, Biao Liu, Yibin Tan, Hai Yu

引用次数: 0

Effect of velocity ratio and Mach number on thin lip coaxial jet 速度比和马赫数对薄唇同轴射流的影响

IF 0.9 4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-11-16 DOI: 10.1515/tjj-2023-0086

Irish Angelin Scwartz, Naren Shankar Rathakrishnan, Sathish Kumar Kumar, Vijayaraja Kengaiah, R. Ethirajan

{"title":"Effect of velocity ratio and Mach number on thin lip coaxial jet","authors":"Irish Angelin Scwartz, Naren Shankar Rathakrishnan, Sathish Kumar Kumar, Vijayaraja Kengaiah, R. Ethirajan","doi":"10.1515/tjj-2023-0086","DOIUrl":"https://doi.org/10.1515/tjj-2023-0086","url":null,"abstract":"Abstract The effect of nozzle lip thickness and velocity ratio on coaxial subsonic jet mixing, at different Mach numbers, has been studied experimentally and numerically. Decay of coaxial subsonic jets emanating from coaxial nozzles of lip thickness 0.7, 1.7 and 2.65 mm with velocity ratio (VR) from 0.2 to 1.0 at primary jet exit Mach numbers of 0.6, 0.8 and 1.0 has been studied. Free jet without co-flow (VR0) was also studied for comparison. Jet centerline Mach number decay, turbulence and velocity variation in the radial direction are analyzed. The results show that mixing the coaxial jet at a low-velocity ratio is better than a high-velocity ratio, at all Mach numbers of the present study. The nozzle lip thickness has a significant influence on the secondary jet. Mixing of the jet in the presence of VR0.2 coaxial jet is found to be the highest. Characteristic decay of Mach 0.8 and 1.0 jet for lip thickness 1.7 and 2.65 mm is faster than lip thickness 0.7 mm. For a given lip thickness, increasing of velocity ratio is found to retard the mixing between primary and secondary jets.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"32 3","pages":""},"PeriodicalIF":0.9,"publicationDate":"2023-11-16","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139267346","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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

Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor 直升机/发动机/红外抑制器集成建模与耦合特性分析

4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-11-14 DOI: 10.1515/tjj-2023-0060

Benlin Cheng, Xing Huang, Chuang Ji, Wencheng Zhong, Haibo Zhang

{"title":"Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor","authors":"Benlin Cheng, Xing Huang, Chuang Ji, Wencheng Zhong, Haibo Zhang","doi":"10.1515/tjj-2023-0060","DOIUrl":"https://doi.org/10.1515/tjj-2023-0060","url":null,"abstract":"Abstract In order to explore the influence of the infrared stealth technology on the performance of the integrated helicopter/engine system, an integrated modeling method of helicopter/engine/infrared suppressor is proposed. Firstly, based on the power calculation model of the helicopter, combined with the high-precision turboshaft engine component-level model, an integrated simulation platform is built, which takes into account the nonlinear characteristics. Then, the aerodynamic characteristics of infrared suppressors under different engine operation states are studied by CFD numerical computation method, and the infrared radiation characteristics are obtained through combining the positive and negative ray tracing method and narrow band model method. Ultimately, the utilization of the power turbine outlet stagnation pressure is employed as the pivotal interface linking the turboshaft engine and the infrared suppressor in order to formulate an integrated model encompassing the helicopter, engine, and infrared suppressor subsystems. The simulation results demonstrate that compared with the conventional exhaust system, the application of the infrared suppressor greatly enhances the stealth performance of the helicopter, but also results in the unexpected decrease in engine output power. Moreover, the specific fuel consumption of the turboshaft engine increase and the compressor surge margin decreases in case of the consistent flight condition.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"26 19","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134991798","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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

Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow 可调速机匣端部位置对跨声速压气机转子叶尖泄漏流动的影响

4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-11-01 DOI: 10.1515/tjj-2023-0016

Jiayi Zhao, Wanyang Wu, Jingjun Zhong

引用次数: 0

Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0 标签形状、长度和位置对马赫2.0时过度膨胀自由射流的影响

4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-10-18 DOI: 10.1515/tjeng-2023-0079

Srinivasa Rao Lavala, Partha Mondal, Sudip Das

{"title":"Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0","authors":"Srinivasa Rao Lavala, Partha Mondal, Sudip Das","doi":"10.1515/tjeng-2023-0079","DOIUrl":"https://doi.org/10.1515/tjeng-2023-0079","url":null,"abstract":"Abstract Experiments have been carried out to investigate the over expanded free jet at Mach number 2.0 without and with tabs of different cross-sectional shapes, tab length penetration into the jet core defined as blockage ratio, and symmetrical and asymmetrical placement of tabs at the jet exit. The cross-sectional shapes such as triangular, square, and circular have been studied with the penetration depth of 3 %, 7 %, and 11 % blockage. The Pitot tube and Schlieren flow visualization were carried out in experiments. The basic features of the jet with Mach disk, shock cell, and its distortion with the adoption of tabs at various nozzle pressure ratios indicate a definite influence that helps in the reduction of the core jet length. This characteristic is also influenced by changes in tab cross-section and length of penetration. Since the basic jet has three-dimensional structures, the asymmetric placement of tabs is beneficial compared to the symmetric orientation of tabs. The jet width increases with adoption of these tabs and different shapes. Whereas, a maximum core jet length reduction of the order of 60 % could be achieved using the present techniques.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"56 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135943849","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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

Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0 标签形状、长度和位置对马赫2.0时过度膨胀自由射流的影响

4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-10-18 DOI: 10.1515/tjj-2023-0079

Srinivasa Rao Lavala, Partha Mondal, Sudip Das

{"title":"Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0","authors":"Srinivasa Rao Lavala, Partha Mondal, Sudip Das","doi":"10.1515/tjj-2023-0079","DOIUrl":"https://doi.org/10.1515/tjj-2023-0079","url":null,"abstract":"Abstract Experiments have been carried out to investigate the over expanded free jet at Mach number 2.0 without and with tabs of different cross-sectional shapes, tab length penetration into the jet core defined as blockage ratio, and symmetrical and asymmetrical placement of tabs at the jet exit. The cross-sectional shapes such as triangular, square, and circular have been studied with the penetration depth of 3 %, 7 %, and 11 % blockage. The Pitot tube and Schlieren flow visualization were carried out in experiments. The basic features of the jet with Mach disk, shock cell, and its distortion with the adoption of tabs at various nozzle pressure ratios indicate a definite influence that helps in the reduction of the core jet length. This characteristic is also influenced by changes in tab cross-section and length of penetration. Since the basic jet has three-dimensional structures, the asymmetric placement of tabs is beneficial compared to the symmetric orientation of tabs. The jet width increases with adoption of these tabs and different shapes. Whereas, a maximum core jet length reduction of the order of 60 % could be achieved using the present techniques.","PeriodicalId":50284,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135884687","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"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

Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control 基于直接性能参数闭环控制的串联TBCC发动机模式转换控制系统设计

4区工程技术

International Journal of Turbo & Jet-Engines Pub Date : 2023-10-12 DOI: 10.1515/tjj-2023-0069

Zhihua Xi, Cheng Chen, Ming Chen, Haibo Zhang

引用次数: 0