Numerical simulation of the flow in the rotation cavities of turbopump assembly

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.

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Hydraulic losses in the initial section of a flow parts of at aggregates of liquid rocket engines

Жуйков

Zuev

Nazarov

et al. 2020

IOP Conf. Ser.: Mater. Sci. Eng.

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On Computing Losses in Blading Sections of Liquid Rocket Engine Pressurisation Stations

2020

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Designing more sophisticated contemporary liquid rocket engines requires a precise understanding of the hydrodynamics in the blading sections of the pressurisation station, which is most often a turbopump. Friction loss in blade passages and outlets forms a significant proportion of all losses. The paper shows that it is necessary to account for the initial region of hydrodynamically unbalanced flow in the boundary layer, which is most characteristic of relatively short passages in blading sections of liquid rocket engine turbopumps. We performed the analysis required to select friction drag laws for components of pressurisation station blading sections. We considered and proposed a method for numerically integrating a system of equations to determine the variation in characteristic thickness of a spatial boundary layer and friction loss, accounting for the inertial component of the flow core velocity, depending on which flow modes occur in the components of pressurisation station blading sections in a liquid rocket engine. We show that it is necessary to correctly select the friction laws and to take the initial region into account so as to precisely determine the power parameters

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Axial Gas-Dynamic Forces in a Compact Centrifugal Compressor

Evgen’ev

Futin

2018

Russ. Aeronaut.

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Numerical simulation of the flow in the rotation cavities of turbopump assembly

Cited by 3 publications

References 4 publications

Hydraulic losses in the initial section of a flow parts of at aggregates of liquid rocket engines

Hydraulic losses in the initial section of a flow parts of at aggregates of liquid rocket engines

On Computing Losses in Blading Sections of Liquid Rocket Engine Pressurisation Stations

Axial Gas-Dynamic Forces in a Compact Centrifugal Compressor

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