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Grigore Cican, Tiberius-Florian Frigioescu, Daniel-Eugeniu Crunteanu and Laurentiu Cristea
This paper explores the implementation of an ejector to a micro turbojet engine and analysis of the advantages in terms of acoustic and thrust/fuel consumption. Starting with the analytical equations and a series of numerical simulations, the optimal eje...
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Chen Wang, Xian Du and Ximing Sun
To investigate the performance potential of the aero-propulsion system and the problem of control mode conversion, this paper takes the inlet/engine integrated component-level model as the research object, and a performance-seeking control (PSC) scheme b...
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Oliver Sjögren, Tomas Grönstedt, Anders Lundbladh and Carlos Xisto
In modern turbofan engines, the bypass section of the fan stage alone provides the majority of the total thrust required in cruise, and the size of the fan has a considerable effect on the overall engine weight and nacelle drag. Thrust requirements in di...
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Yangjing Wang, Jinquan Huang, Muxuan Pan and Wenxiang Zhou
The variable cycle engine switches working modes by way of changing variable-geometry components to achieve the dual advantages of high unit thrust and low specific fuel consumption. Due to the lack of a large amount of rig test data and the complex mode...
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Hamidreza Abedi, Carlos Xisto, Isak Jonsson, Tomas Grönstedt and Andrew Rolt
The investigation of the various heat management concepts using LH2 requires the development of a modeling environment coupling the cryogenic hydrogen fuel system with turbofan performance. This paper presents a numerical framework to model hydrogen-fuel...
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Wenhao Tan, Longxi Zheng, Jie Lu and Zhiyi Xiao
In order to obtain the dynamic operating characteristics of a pulse detonation turbine engine (PDTE), a transient model is established considering the shaft dynamics and the volumetric effect of the components in the PDTE. The accuracy of the model is ve...
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Shihai Yang, Bo Xu and Xin Li
For geostationary orbit transfers, a long duration is required using electric propulsion and a large propellant mass is needed with chemical propulsion. Hybrid transfers can achieve a balance between the fuel consumption and transfer time. In this paper,...
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Sim Sing Mei, Aslina Anjang Ab Rahman, Mohd Shukur Zainol Abidin and Nurul Musfirah Mazlan
A comparison of d2 law and penetration length of biofuels with Jet?A through the incorporation of fuel properties and actual combustor inlet data at various flight trajectories is presented. This study aims to identify fuel properties and flight operatin...
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Evangelia Maria Thoma, Tomas Grönstedt and Xin Zhao
Aircraft and engine technology have continuously evolved since their introduction and significant improvement has been made in fuel efficiency, emissions, and noise reduction. One of the major issues that the aviation industry is facing today is pollutio...
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James Large and Apostolos Pesyridis
In this study, the on-going research into the improvement of micro-gas turbine propulsion system performance and the suitability for its application as propulsion systems for small tactical UAVs (<600 kg) is investigated. The study is focused around the ...
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