Numerical simulations of dynamic loads in aviation combined pumps

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Abstract

Modern cryostatting systems find important applications in power and space transportation systems. The cryostatting system is a closed hydraulic loop for the thermal management and control of thermal modes of supercon- ducting cable lines, cryogenic rocket and space units fuel tanks. The working medium is liquid nitrogen. One of the main components of such a system is the criorefrigirator. In the criorefrigirator compression scheme is used with following expansion of neon in the turboexpander, machine with gas-static bearings. Urgent task in the design phase is to determine the pressure fluc- tuations in the flow of the turbo expander and dynamic loading of the struc- ture. This paper presents the numerical simulation of unsteady gas-dynamic processes in the turbo expander radial turbine flow. Expansion turbine con- sists of mounted on the same shaft the radial turbine impeller and centrifugal compressor first stage, that also serves as a gas-dynamic brake. Gas is fed to the expander casing through two pipelines. Further, it is accelerated in the nozzle cascade and enters the turbine impeller blades. After expansion and reduction the temperature, the exhaust gas passes through the axial diffuser. Rotor speed is 25,200 rev / min. The geometry of the computational domain is developed in order to capture the main features of the flow in the working fluid cavity, including the geometry of fourteen working blades and eight vanes of the nozzle cascade. The computational domain is divided into three subregions: the casing of the nozzle cascade, rotor and exhaust part. The problem is solved with the use of so-called sliding surfaces which serve for transmitting the data from the rotor, where the calculation is carried out in a rotating coordinate system into the stator zone accounting an angular dis- placement and sub-grid interpolation. Time step chosen from the condition to ensure the angular displacement in one time step within a single cell of the computational grid. The instantaneous velocity, pressure, temperature and Mach number fields are obtained with calculations. Few points in the nozzle vane channel oblique zones are selected to fix pressure pulsations. The spectral analysis of the data reveal that the tonal component with blades passing frequency dominates the spectra of pressure pulsations, its ampli- tude is above 7000 Pa. Calculation of loading on nozzle blade gives the am- plitude of force 2 N and amplitude of momentum 0.03 N m

About the authors

D. V. Klimenko

Moscow Aviation Institute (National Research University)

Email: irico.harmony@gmail.com
Russian Federation

S. F. Timushev

Moscow Aviation Institute (National Research University)

Email: irico.harmony@gmail.com
Russian Federation

V. P. Firsov

Moscow Aviation Institute (National Research University)

Email: irico.harmony@gmail.com
Russian Federation

I. V. Antyukhov

Moscow Aviation Institute (National Research University)

Author for correspondence.
Email: irico.harmony@gmail.com
Russian Federation

References


Copyright (c) 2015 Journal of Dynamics and Vibroacoustics


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