Dynamics of the flow in the sections of the elements of the supply path of the turbopump unit of the LRE

Sections of dynamically non-stabilized flows specific for elements of flow parts of turbo pump assemblies of liquid-propellant rocket engines are considered. Sections of cylindrical variable cross-section, rectangular variable crossection, rotational flows in cavities with stationary walls, stationary and rotating walls are analyzed. Specific elements include: delivery and discharge assemblies, side cavities between rotor and stator, cavities of hydrodynamic seals and elements of interblade channel of centrifugal type pumps and gas turbines. Due to specific features of operating and design parameters, initial sections of dynamically nonstabilized flows are dominant in flow parts of delivery assemblies. These sections have significant influence on energy parameters of the assembly and affect heat exchanging processes and, as a consequence, reliability of constructional elements. Both laminar and turbulent flow regimes of the working fluid are realized in specific elements of delivery systems. With the use of methods of three-dimensional boundary layer theory, specific thicknesses of boundary layer such as thickness of dynamic boundary layer, displacement thickness and momentum loss thickness are determined. Dependences for determination of flow core velocities, necessary for evaluation of losses due to the length of specific sections, are obtained. Proper selection of friction laws and velocities profiles in the boundary layer and consideration of initial section is necessary for the purposes of reliable determination of energy parameters. Obtained dependences consider velocity distribution profile in the boundary layer on specific sections of laminar and turbulent regimes cases.