Xuanfei Yu
Harbin Institute of Technology
9 Papers
Xuanfei Yu is an academic researcher from Harbin Institute of Technology. The author has contributed to research in topics: Brayton cycle & Propulsion. The author has an hindex of 6, co-authored 9 publications.
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Papers
Precooler-design & engine-performance conjugated optimization for fuel direct precooled airbreathing propulsion
Xuanfei Yu,Cong Wang,Daren Yu +2 more
TL;DR: The results show that precooler design is a tradeoff between the optimization objectives considered, whereas larger intake efficiency is extremely preferred for precooled cycles from not only the performance side of the engine, but more importantly, the geometryside of the precoolser.
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Minimization of entropy generation of a closed Brayton cycle based precooling-compression system for advanced hypersonic airbreathing engine
Xuanfei Yu,Cong Wang,Daren Yu +2 more
TL;DR: In this paper, a conjugated optimization coupled with heat exchanger design was performed to evaluate the performance level that can be achieved under the state of technologies, and the results indicated that irreversibility of the precooling-compression system (PCS) can be reduced but at the penalty of heavier and larger size of heat exchangers.
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Thermodynamic analysis of the influential mechanism of fuel properties on the performance of an indirect precooled hypersonic airbreathing engine and vehicle
TL;DR: In this article, a unified engine model was developed for analysis, through which it indicates that besides the properties commonly known, the triple point temperature and stoichiometric heat capacity of the fuel are also crucial to efficient engine operation.
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Configuration optimization of the tandem cooling-compression system for a novel precooled hypersonic airbreathing engine
Xuanfei Yu,Cong Wang,Daren Yu +2 more
TL;DR: Assisted with the multi-segment precooling scheme, the schemes can bring about even larger extent of fuel savings and air precoolsing depth, higher working fluid and air side pressure ratios, and ultimately considerable gains in engine performance.
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Thermodynamic spectrum of direct precooled airbreathing propulsion
TL;DR: In this article, a unified cycle model for the fuel direct precooled engines was proposed to provide a consistent thread of insight for the engine family, and performance evaluation and optimization based on the numerical model were completed for three typical cycles under the flight condition of Mach 5.0 with the dynamic pressure q 0 − 45 kPa.
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