Computational research of parameters of cryogenic propellant system for high-speed aircraft

Abstract

Utilization of cryogenic fuels (condensed natural gas, liquid hydrogen or propane, etc) appears to be promising for aircraft engine. The urgency of switching to cryogenic fuels is due to their high heat of combustion, cooling capacity, environmental safety, significant natural reserves and low cost. The task of the work is modeling and thermal-hydraulic optimization of the cryogenic fuel system by reference to specific features of its use in the high-speed aircraft and in particular: long endurance, high heat-transfer intensity, variety of operation conditions, alternating G-loading, etc. To solve the presented scientific problem, the mathematical model and the parameters calculation procedure of cryogenic fuel system have been developed, which makes it possible to carry out parametric and optimization studies in a wide range of operational conditions. The work presents the results on the selection of cryogenic fuel system parameters for a advanced high-speed aircraft on cryogenic methane. The main mechanisms of the various factors influence on the fuel system mass characteristics and the losses by fuel gasification have been obtained.