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Axial Force Measurement of Gas Foil Thrust Bearings Supporting a Turbo-compressor
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Gas foil thrust bearings (GFTBs) are aerodynamic bearings that use gas as a lubricant to support axial forces in noncontact states. To enhance the load support performance of GFTBs, researchers conduct studies requiring experimental load measurements in mechanical systems for verification. This study measures the thrust of a high-speed turbo-compressor supported by a gas-foil thrust bearing. We examine the effect of temperature changes on the load cell installed inside the compressor before the experiment. First, we supply heat to the compressor using a heating gun to stabilize the load cell temperature. We then apply a static load using a push-pull gauge. Next, we derive the load cell temperature compensation equation based on the difference between the measured and applied loads as temperature varies. The results show that when maintaining the rotor speed at 80 krpm before stopping, the measured load gradually decreases and converges to -108 N, which is lower than the initial 0 N. This decline is owing to the temperature increase in the load cell near the bearing due to the viscous shear friction between the bearing and thrust runner during rotation. Finally, after applying temperature compensation, the thrust increases with increasing rotational speed of the rotor.
Abstract
Gas foil thrust bearings (GFTBs) are aerodynamic bearings that use gas as a lubricant to support axial forces in noncontact states. To enhance the load support performance of GFTBs, researchers conduct studies requiring experimental load measurements in mechanical systems for verification. This study measures the thrust of a high-speed turbo-compressor supported by a gas-foil thrust bearing. We examine the effect of temperature changes on the load cell installed inside the compressor before the experiment. First, we supply heat to the compressor using a heating gun to stabilize the load cell temperature. We then apply a static load using a push-pull gauge. Next, we derive the load cell temperature compensation equation based on the difference between the measured and applied loads as temperature varies. The results show that when maintaining the rotor speed at 80 krpm before stopping, the measured load gradually decreases and converges to -108 N, which is lower than the initial 0 N. This decline is owing to the temperature increase in the load cell near the bearing due to the viscous shear friction between the bearing and thrust runner during rotation. Finally, after applying temperature compensation, the thrust increases with increasing rotational speed of the rotor.
참고문헌 (9)
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