Open AccessHydraulic losses in the initial section of a flow parts of at aggregates of liquid rocket engines
Author(s) -
Д А Жуйков,
Alexander Zuev,
В. П. Назаров,
M I Tolstopyatov,
Э В Ходенкова
Publication year - 2020
Publication title -
iop conference series. materials science and engineering
Language(s) - English
Resource type - Journals
eISSN - 1757-899X
pISSN - 1757-8981
DOI - 10.1088/1757-899x/862/2/022034
Subject(s) - mechanics , flow (mathematics) , liquid propellant rocket , rocket (weapon) , rocket engine , boundary layer , process (computing) , control theory (sociology) , mechanical engineering , engineering , computer science , aerospace engineering , physics , control (management) , propellant , artificial intelligence , operating system
The article deals with the need for accurate hydraulic losses determination along the length of the flow part in the process of designing units for supplying liquid rocket engines (LRE). The dependencies that are usually used, as a rule, are of a criterion-empirical nature and are not suitable for their application, taking into account the tendency of an increase in the rotating speed of turbo-pumping LRE supply units to 100,000 r.p.m. The analysis necessary to select the friction resistance laws for the flow part elements of the rocket engine supply units was carried out. A numerical integration equation system method to determine the variation in the characteristic thicknesses of the spatial boundary layer along the channel length in the initial section of the flow and hydraulic losses (taking into account the inertial component of the flow core velocity) was considered and proposed, depending on the current flow regimes in the flow path elements of the LRE supply units.