Session: 01-10 Modelling, Simulation and Validation II

Paper Number: 122932

122932 - Research on Calculation Method of Variable Specific Heat Performance of Wide-Speed Range Aeroengine 

    With the increasing demand for hypersonic maneuvering in the future, it is particularly important to develop wide speed region engine technology, and the wide-range incoming flow conditions will cause significant changes in aero-thermal processes. The method of constant specific heat is generally used in the aerodynamic performance calculation of traditional aeroengine, but this method is no longer suitable for the performance calculation of wide speed domain aeroengine, so it is necessary to develop a calculation method of variable specific heat for wide speed domain aeroengine. The engineering thermodynamic properties were calculated using theta function, and have compared with the published results of Gas Turbine Performance and JANAF, the results show that the difference is less than 10%. Because The engineering thermodynamic properties were usually fitted by polynomial, Qin Jiushao algorithm was adopted to improve the calculation efficiency. The calculation method based on constant specific heat assumption and velocity coefficient was no longer used in the calculation of aerodynamic properties. Instead, the calculation method of energy conservation and isentropic process and numerical method of false position were used to obtain the calculation method of aeroengine performance under the condition of wide speed domain. The calculation results show that under the condition of 30km 5Ma, for the stagnation process, the total temperature difference is about 10%, the total pressure difference is more than 25%, for the expansion process, under the condition of fully expanded and flow rate of 125kg/s, the critical section area difference is about 25%, and for engine performance, the thrust difference is about 8%, and the specific fuel consumption difference is about 12%.

Presenting Author: Huipeng Du Beihang University

Presenting Author Biography: Huipeng Du received the B.S. degree in thermal and power engineering from University of Science and Technology of China, Hefei, China, in 2014 and the M.S. degree in power engineering from University of Science and Technology of China, Hefei, China, in 2017. He is currently working toward the Ph.D. degree in power machinery and engineering with school of Beihang University, Beijing, China. His research interests include aeroengine performance and air sytem.

Authors:

Huipeng Du Beihang University
Chuankai Liu Beihang University