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International Journal of Turbo & Jet-Engines最新文献

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Research on the design method of mode transition control law for Ma6 external parallel TBCC engine Ma6 外置并联 TBCC 发动机模式转换控制规律设计方法研究
International Journal of Turbo & Jet-Engines Pub Date : 2024-02-09 DOI: 10.1515/tjj-2024-0003
Guiqian Jiao, Wenyan Song, Xianglong Zeng, Yu Fu, Jianping Li
{"title":"Research on the design method of mode transition control law for Ma6 external parallel TBCC engine","authors":"Guiqian Jiao, Wenyan Song, Xianglong Zeng, Yu Fu, Jianping Li","doi":"10.1515/tjj-2024-0003","DOIUrl":"https://doi.org/10.1515/tjj-2024-0003","url":null,"abstract":"\u0000 To achieve a fast and reliable mode transition of the Ma 0–6 external parallel TBCC engine, a design method for the transition state control law is developed. The design parameters of the TBCC engine are obtained based on the mission requirements of hypersonic aircraft. For the key mode transition process of the combination engine, a segmented mode transition strategy is formulated with the objectives of smooth thrust and continuous flow. The mode transition control law of the combination engine is designed and optimized using the Hooke-Jeeve Direct Search Method. The results demonstrate that the proposed design method for the mode transition control law can effectively enable a fast and smooth mode transition of the combination engine, with a total duration of 7 s. During the mode transition process, the total thrust fluctuation during the transition from the turbofan windmill state to the turbofan shutdown state is the largest, and the maximum relative error between the total thrust and the expected value during the mode transition process is 0.4 %.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"50 6","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139895723","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 the design method of mode transition control law for Ma6 external parallel TBCC engine Ma6 外置并联 TBCC 发动机模式转换控制规律设计方法研究
International Journal of Turbo & Jet-Engines Pub Date : 2024-02-09 DOI: 10.1515/tjj-2024-0003
Guiqian Jiao, Wenyan Song, Xianglong Zeng, Yu Fu, Jianping Li
{"title":"Research on the design method of mode transition control law for Ma6 external parallel TBCC engine","authors":"Guiqian Jiao, Wenyan Song, Xianglong Zeng, Yu Fu, Jianping Li","doi":"10.1515/tjj-2024-0003","DOIUrl":"https://doi.org/10.1515/tjj-2024-0003","url":null,"abstract":"\u0000 To achieve a fast and reliable mode transition of the Ma 0–6 external parallel TBCC engine, a design method for the transition state control law is developed. The design parameters of the TBCC engine are obtained based on the mission requirements of hypersonic aircraft. For the key mode transition process of the combination engine, a segmented mode transition strategy is formulated with the objectives of smooth thrust and continuous flow. The mode transition control law of the combination engine is designed and optimized using the Hooke-Jeeve Direct Search Method. The results demonstrate that the proposed design method for the mode transition control law can effectively enable a fast and smooth mode transition of the combination engine, with a total duration of 7 s. During the mode transition process, the total thrust fluctuation during the transition from the turbofan windmill state to the turbofan shutdown state is the largest, and the maximum relative error between the total thrust and the expected value during the mode transition process is 0.4 %.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":" 7","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139893331","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
A new schedule method for compact propulsion system model 紧凑型推进系统模型的新时间表方法
International Journal of Turbo & Jet-Engines Pub Date : 2024-02-09 DOI: 10.1515/tjj-2023-0099
Yu Bai, Zhengchen Zhu, Zhigui Xu, Haoran Guo
{"title":"A new schedule method for compact propulsion system model","authors":"Yu Bai, Zhengchen Zhu, Zhigui Xu, Haoran Guo","doi":"10.1515/tjj-2023-0099","DOIUrl":"https://doi.org/10.1515/tjj-2023-0099","url":null,"abstract":"\u0000 The PSC (Performance Seeking Control) based on CPSM (Compact Propulsion System Model) has been verified by NASA. However, the CPSM has poor accuracy at off-design points. Therefore, a new basepoint schedule method is proposed to improve the CPSM accuracy at off-design points. At the off-design point, the thermodynamic parameters which is a function of temperature is an importance factor that influence the accuracy of model based on parameter corrections. Therefore, the temperature of fan inlet is taken into account during scheduling the basepoint vector. The simulations have shown that the accuracy of CPSM is at its best when the engine operates at a point where the temperature of the fan inlet is equal to the one of the basepoint. With the increase or decrease of the temperature of the fan inlet, the modeling errors of CPSM will increase. The simulations also demonstrate that the relative errors of the improved CPSM decrease significantly compared to those of the conventional CPSM at the off-design point.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"34 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139894803","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
Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins 双壁冷却配置的共轭传热分析，包括喷流撞击和带保形销的膜孔
International Journal of Turbo & Jet-Engines Pub Date : 2024-02-07 DOI: 10.1515/tjj-2023-0106
Chenlin Chen, Yuting Jiang, Haosu Zhang, Liangchen Dong, Zitong Zhang
{"title":"Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins","authors":"Chenlin Chen, Yuting Jiang, Haosu Zhang, Liangchen Dong, Zitong Zhang","doi":"10.1515/tjj-2023-0106","DOIUrl":"https://doi.org/10.1515/tjj-2023-0106","url":null,"abstract":"\u0000 A double-wall cooling configuration including impingement holes and film holes with conformal pins is studied by CFD numerical simulation in this paper. The influences of three different injection directions of film holes at six blowing ratios ranging from 0.4 to 2.5 on conjugate heat transfer characteristic are investigated. Impingement-only arrangements with corresponding pin directions are adopted to illustrate the film cooling gains and the impingement cooling contribution. The results indicate that the effect of different pin directions on overall cooling effectiveness is non-significant. At low blowing ratio, the forward injection arrangement has higher overall cooling effectiveness since greater gain of film cooling, and is transcended by reverse injection arrangement as coolant supplement increases. Moreover, although the cooling effectiveness for normal injection case is the lowest within the whole range of mass flow rate, it possesses the most uniform distribution of cooling effectiveness in downstream region at high blowing ratio.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"43 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139895345","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
Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization 基于轨迹优化的涡轮联合循环发动机推力匹配和优化设计
International Journal of Turbo & Jet-Engines Pub Date : 2024-02-02 DOI: 10.1515/tjj-2023-0018
JianFeng Zhu, YingChen Liu, Wenguo Luo, Feng Guo
{"title":"Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization","authors":"JianFeng Zhu, YingChen Liu, Wenguo Luo, Feng Guo","doi":"10.1515/tjj-2023-0018","DOIUrl":"https://doi.org/10.1515/tjj-2023-0018","url":null,"abstract":"\u0000 Based on the trajectory optimization method of the Gauss pseudospectral, an aircraft/engine matching method is established for the turbine-based combined cycle (TBCC) engine. For a horizontal-takeoff hypersonic aircraft designed at Mach 5, a thrust-matching analysis of the TBCC engine is performed, and a rocket is integrated for further optimization design. The results show that the aircraft for boost missions should adopt the TBCC thrust with a takeoff thrust-to-weight ratio of 99.8 % to reduce the acceleration time and fuel consumption. In contrast, due to the low thrust-to-weight ratio of the TBCC engine, a high-thrust TBCC increases the inert weight in the cruise phase. Therefore, the aircraft designed for cruise missions should adopt the takeoff thrust-to-weight ratio of 92.0 %. Introducing a rocket whose maximum thrust is 10 % of the takeoff weight could assist the aircraft in overcoming the problem of the “thrust pinch” during the transonic and mode transition. With the assistance of rockets, the optimal takeoff thrust-to-weight ratio is 65.3 % for cruise aircraft, and the cruise range is increased by 18 %. While for the boost aircraft, adopting an optimal TBCC of 86.8 % takeoff thrust-to-weight ratio, the introduced rocket could reduce the fuel consumption and the TBCC engine weight by 4 %.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"20 7","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139896494","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
Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization 基于轨迹优化的涡轮联合循环发动机推力匹配和优化设计
International Journal of Turbo & Jet-Engines Pub Date : 2024-02-02 DOI: 10.1515/tjj-2023-0018
JianFeng Zhu, YingChen Liu, Wenguo Luo, Feng Guo
{"title":"Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization","authors":"JianFeng Zhu, YingChen Liu, Wenguo Luo, Feng Guo","doi":"10.1515/tjj-2023-0018","DOIUrl":"https://doi.org/10.1515/tjj-2023-0018","url":null,"abstract":"\u0000 Based on the trajectory optimization method of the Gauss pseudospectral, an aircraft/engine matching method is established for the turbine-based combined cycle (TBCC) engine. For a horizontal-takeoff hypersonic aircraft designed at Mach 5, a thrust-matching analysis of the TBCC engine is performed, and a rocket is integrated for further optimization design. The results show that the aircraft for boost missions should adopt the TBCC thrust with a takeoff thrust-to-weight ratio of 99.8 % to reduce the acceleration time and fuel consumption. In contrast, due to the low thrust-to-weight ratio of the TBCC engine, a high-thrust TBCC increases the inert weight in the cruise phase. Therefore, the aircraft designed for cruise missions should adopt the takeoff thrust-to-weight ratio of 92.0 %. Introducing a rocket whose maximum thrust is 10 % of the takeoff weight could assist the aircraft in overcoming the problem of the “thrust pinch” during the transonic and mode transition. With the assistance of rockets, the optimal takeoff thrust-to-weight ratio is 65.3 % for cruise aircraft, and the cruise range is increased by 18 %. While for the boost aircraft, adopting an optimal TBCC of 86.8 % takeoff thrust-to-weight ratio, the introduced rocket could reduce the fuel consumption and the TBCC engine weight by 4 %.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"21 9","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139893303","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
Parametric analysis of thermal cycle of a short take-off and vertical landing engine 短距起飞和垂直着陆发动机热循环参数分析
International Journal of Turbo & Jet-Engines Pub Date : 2024-02-02 DOI: 10.1515/tjj-2023-0054
Zhihan Mo, Dengji Zhou, Xun Shen
{"title":"Parametric analysis of thermal cycle of a short take-off and vertical landing engine","authors":"Zhihan Mo, Dengji Zhou, Xun Shen","doi":"10.1515/tjj-2023-0054","DOIUrl":"https://doi.org/10.1515/tjj-2023-0054","url":null,"abstract":"\u0000 Short take-off/vertical landing (STOVL) engine is an emerging power source for fighter planes that can perform takeoff and landing operations in tight quarters. As the aforementioned function requires specific component design and matching, it is vitally necessary to study the impacts of various component states on engine performance and stability. This paper develops a performance model for STOVL engines based on nonlinear component models and validates the modelʼs correctness. Variable component working conditions and settings are altered, engine performance is forecasted and observed, and the mechanism underlying this trend is investigated. The results indicate that the performance of the STOVL engine is greatly influenced by the design parameters of the gas path, such as the bypass ratio and the injection volume of the roll nozzle, and is highly dependent on the correct adjustment of the rear bypass injector and the throat area of the nozzle.","PeriodicalId":517068,"journal":{"name":"International Journal of Turbo & Jet-Engines","volume":"83 2","pages":""},"PeriodicalIF":0.0,"publicationDate":"2024-02-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139897062","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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