Radial-Circumferential Flow in a Microturbine of a Spacecraft Two-Phase Thermal Control System

Aeronautical and Space-Rocket Engineering


Аuthors

Shilkin O. V.1*, Shevchenko Y. N.2**, Delkov A. V.2***, Kishkin A. A.2****, Snetkov P. A.2*****, Abdullaev M. U.2

1. Compani «Information satellite systems of academician M.F. Reshetnev», 52, Lenin str., Zheleznogorsk, Krasnoyarsk region, 662972, Russia
2. Siberian State University of Science and Technology named after academician M.F. Reshetnev, 31, Krasnoyarsky Rabochy av., Krasnoyarsk, 660014, Russia

*e-mail: shilkin@iss-reshetnev.ru
**e-mail: gift_23j@mail.ru
***e-mail: delkov-mx01@mail.ru
****e-mail: spsp99@mail.ru
*****e-mail: snetkov@list.ru

Abstract

In the last decade, an anticipatory reserve into the thermal control systems (TCS) basic elements, which allowed the TCS forming to any problem solution with topological linkage of all of the target equipment spectrum was created within the framework of the research and development work “Thermal Control System with Two-Phase Circuit” (TCS TPC), which encompassed enterprises of the Russian Space Agency. This combined approach to the elements integration allows 2-3 times heat transfer from the equipment to the emitting radiators effectiveness increase with mass savings, namely 1.5-2 times for the heat release levels up to 15 kW, and 3-5 times for the heat release levels up to 30 kW compared to the conventional heat pipes and liquid circuits based TCSs. The results of the research demonstrate the expediency of utilizing the thermal energy of the coolant vapor removed by the TCS TPC employing energy installations based on micoturbines for the prospective spacecraft with high heat generation levels of more than 7 kW.
Theoretical and laboratory research with the experimental installations conducted in Russia and abroad prove both technical expediency and relevance of such kind of work. The level of the heat energy regeneration into eclectic energy may reach 18% at low (up to 4 kg) mass costs. As the result, the required heat sink and solar panel areas will decrease by 12-14%, whereby the efficiency of the power plants utilization increases with the spacecraft heat generation increasing.
It should be noted that for both active and reactive types of turbines nozzle or guide assembly for the high-speed turbines accomplished in the form of nozzle arrays (in the blade crown) is the crucial element, which forms the flow circumferential direction, ensuring circumferential operation of the impeller. For the low-speed and low-flow machines the one nozzle (nozzle tangential channel) is being accomplished.
A part of the design works requires computational modeling during the swirling flows transporting in the radial direction from the external tangential inlet to the turbine impeller inlet surface, which defines the need for theoretical and experimental study of the problem as one of the main determinants of the flow energy at the impeller inlet.
The article considers transformations of the equations of change in the circumferential amount of gas motion in the boundary conditions of a radially end cavity with fixed walls, with an adiabatic flow to the center. Under the assumptions of the flow axial symmetry and the axial gap constancy, integration of the equations of motion in cylindrical coordinates by the magnitude of the axial gap was performed. With account for the assumptions of the spatial boundary layer about characteristic thicknesses, solutions were obtained in the form of a system of the two ordinary differential equations in full differentials, which allowed performing their numerical integration under the boundary conditions of a cylindrical end slit. For numerical integration, the system is reduced to the form of two differential equations with expressed derivatives along the channel radius for the static channel p and circumferential velocity constant Cu = UR (const – at the integration step). The authors analyzed the obtained results are proposed possible options for the algorithm improving.

Keywords:

equation of fluid motion in cylindrical coordinates, radially circumferential flow, computational algorithm in finite-difference analogues, turbine inlet unit, coolant steam flow, two-phase temperature control system

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