Radial turbomachine with axial thrust compensation
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United States of America Patent
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Mar 2, 2021
Grant Date -
Apr 25, 2019
app pub date -
Mar 29, 2017
filing date -
Mar 30, 2016
priority date (Note) -
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Abstract
A radial turbomachine with axial thrust compensation includes a rotor disc with main bladed rings. The main bladed rings together with auxiliary bladed rings delimit a plurality of concentric front main chambers at different pressures. A plurality of concentric rear annular main chambers, each in fluid communication with a respective front main chamber and at the same pressure as the respective front main chamber, is delimited between a rear face of the rotor disc and a fixed casing. The concentric front main chambers are delimited by front areas of the rotor disc and concentric rear annular main chambers are delimited by rear annular areas of the rotor disc. All the rear annular areas are identical to the respective front areas except for one, which is a compensation area configured to compensate, at least in part, for the thrust of external pressure acting on the shaft.
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