• Title/Summary/Keyword: gas foil thrust bearing

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Performance Analysis of Gas Foil Journal & Thrust Bearings (가스포일 저널베어링 및 스러스트베어링의 성능해석)

  • Kim Young-Cheol;Han Jeong-Wan;Kim Kyung-Woong
    • Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
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    • pp.267-272
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    • 2003
  • This paper presents a performance analysis model of corrugated bump foil bearings. The analyses for not only 1st generation bump foil journal bearings but also bump foil thrust bearings are performed. Static performances such as load capacity, attitude angle, pressure distribution, foil deflection, and film thickness are accurately estimated by using soft elasto-hydrodynamic analysis technique and finite difference numerical method. Also dynamic performances such as stiffness coefficients and damping coefficients are estimated by perturbation method. The analysis technique may be appliable to rotordynamic analysis, stability analysis, and optimized bearing design.

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On the Bearing-to-Bearing Variability in Experimentally Identified Structural Stiffnesses and Loss Factors of Bump-Type Foil Thrust Bearings under Static Loads (범프 타입 포일 스러스트 베어링의 정하중 구조 강성 및 손실 계수 차이에 관한 실험적 연구)

  • Lee, Sungjin;Ryu, Keun;Jeong, Jinhee;Ryu, Solji
    • Tribology and Lubricants
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    • v.36 no.6
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    • pp.332-341
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    • 2020
  • High-speed turbomachinery implements gas foil bearings (GFBs) due to their distinctive advantages, such as high efficiency, lesser part count, and lower weight. This paper provides the test results of the static structural stiffnesses and loss factors of bump-type foil thrust bearings with increasing preload and bearing deflection. The focus of the current work is to experimentally quantify variability in structural stiffnesses and loss factors among the four test thrust bearings with identical design values and material of the bump and top foil geometries using the same (open-source) fabrication method. A simple test setup, using a rigidly mounted non-rotating shaft and thrust disk, measures the bearing bump deflections with increasing static loads on the test bearing. The inner and outer diameters of the test bearings are 41 mm and 81 mm, respectively. The loss factor, best-representing energy dissipation in the test bearings, is estimated from the area inside the local hysteresis loop of the load versus the bearing deflection curve. The measurements show that structural stiffnesses and loss factors of the test bearings significantly rely on applied preloads and bearing deflections. Local structural stiffnesses of the test bearings increase with applied preloads but decrease with bearing deflections. Changes of loss factors are less sensitive to applied preloads and bearing deflections compared to those of structural stiffnesses. Up to 35% variability in static load structural stiffnesses is found between bearings, while up to 30% variability in loss factors is found between bearings.

Stability Improvement of the Ultra-High Speed Micro Turbocharger Supported by Air Foil Bearings (공기 포일 베어링으로 지지되는 초고속 마이크로 터보차져의 구동 안정성 향상에 관한 연구)

  • Kwak, Yong-Suk;Kim, Chang-Ho;Chung, Jin-Taek;Lee, Yong-Bok
    • Transactions of the Korean Society of Mechanical Engineers A
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    • v.32 no.7
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    • pp.541-548
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    • 2008
  • To improve the operational stability of the 100 Watts class Micro Gas Turbine, the air foil bearing with additional damping material has been investigated. The key of structure is that a viscoelastic material is coated under the top foil. The compliant foil journal bearing and thrust bearing are designed to withstand high load of vibrations at the operational speed 870,000 rpm. Test is executed in room temperature. Rotor has stably operated above 480,000 rpm. It is over 55% of the designed speed 870,000 rpm. Synchronous and subsynchronous vibrations are both well controlled. Vibration amplitude diminished over 50%. With the help of increased damping resulting from the viscoelasticity, the rotor stability of Micro turbocharger has been improved.

Experimental Study on the Load Carrying Performance and Driving Torque of Gas Foil Thrust Bearings (가스 포일 스러스트 베어링의 하중지지 성능 및 구동 토크에 관한 실험적 연구)

  • Kim, Tae Ho;Lee, Tae Won;Park, Moon Sung;Park, Jungmin;Kim, Jinsung;Jeong, Jinhee
    • Tribology and Lubricants
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    • v.31 no.4
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    • pp.141-147
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    • 2015
  • Gas foil thrust bearings (GFTBs) have attractive advantages over rolling element bearings and oil film thrust bearings, such as oil-free operation, high speed stability, and high-temperature operation. However, GFTBs have lower load carrying capacity than the other two types of bearings owing to the inherent low gas viscosity. The load carrying capacity of GFTBs depends mainly on the compliance of the foil structure and the formed hydrodynamic wedge, where the gas pressure field is generated between the top foil and the thrust runner. The load carrying capacity of the GFTBs is very important for the suitable design of oil-free turbomachinery with high performance. The aim of the present study is to identify the characteristics of the load carrying performance of GFTBs. A new test rig for the experimental measurements is designed to provide static loads up to 800 N using a pneumatic cylinder. The maximum operating speed of the driving motor is 30,000 rpm. A series of experimental tests—lift-off test, static load performance test, and maximum load capacity test—estimate the performance of a six-pad GFTB, in terms of the static load, driving torque, and temperature. The maximum load capacity is determined by increasing the static load until the driving torque rises suddenly with a sharp peak. The test results show that the torque and temperature increase linearly with the static load. The estimated maximum load capacity per unit area is approximately 80.5 kPa at a rotor speed of 25,000 rpm. The test results can be used as a design guideline for GFTBs for realizing oil-free turbomachinery.

Rotordynamic Performance Measurements and Predictions of a FCEV Air Compressor Supported on Gas Foil Bearings (가스 포일 베어링으로 지지되는 연료전지 전기자동차용 공기압축기의 회전체동역학적 성능 측정 및 예측)

  • Hwang, Sung Ho;Moon, Chang Gook;Kim, Tae Ho;Lee, Jongsung;Cho, Kyung Seok;Ha, Kyoung-Ku;Lee, Chang Ha
    • Tribology and Lubricants
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    • v.35 no.1
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    • pp.44-51
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    • 2019
  • The paper presents the rotordynamic performance measurements and model predictions of a fuel cell electric vehicle (FCEV) air compressor supported on gas foil bearings (GFBs). The rotor has an impeller on one end and a thrust runner on the other end. The front (impeller side) and rear (thrust side) gas foil journal bearings (GFJBs) are located between the impeller and thrust runner to support the radial loads, and a pair of gas foil thrust bearings are located on both sides of the thrust runner to support the axial loads. The test GFJBs have a partial arc shim foil installed between the top foil and bump strip layers to enhance hydrodynamic pressure generation. During the rotordynamic performance tests, two sets of orthogonally installed eddy-current displacement sensors measure the rotor radial motions at the rotor impeller and thrust ends. A series of speed-up and coast-down tests to 100k rpm demonstrates the dominant synchronous (1X) rotor responses to imbalance masses without noticeable subsynchronous motions, which indicates a rotordynamically stable rotor-GFB system. Finite element analysis of the rotor determines the rotor free-free (bending) natural modes and frequencies well beyond the maximum rotating frequency. The predicted damped natural frequencies and damping ratios of the rotor-GFB system reveal rotordynamic stability over the speeds of interest. The imbalance response predictions show that the predicted critical speeds and rotor amplitudes strongly agree with the test measurements, thus validating the developed rotordynamic model.

A Study on the Characteristics of the Oil-free Turbocharger for Diesel Engine Vehicles (디젤 엔진 차량의 무급유 터보차져의 성능 평가에 관한 연구)

  • Park, Dong-Jin;Kim, Chang-Ho;Lee, Yong-Bok
    • Transactions of the Korean Society of Automotive Engineers
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    • v.16 no.4
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    • pp.47-55
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    • 2008
  • Turbocharger has a main purpose on recycling of the exhaust gas from the engine cylinder. On the basis of the facility characteristics, the turbocharger supported on floating ring bearings has some problems such as the large volume, oil supplement for lubrication and high power loss due to high operating torque. The air foil bearing has been studied as the bearing element to be able to alternate the floating ring bearing without the problems of the floating ring bearing. In this study, the air foil bearing has 2 parts; journal and thrust bearings, and the test facility consists of the engine, exhaust and intake parts. In addiction, the specification of the turbocharger follows a small turbocharger for SUV engine. The engine speed is varied from 750 (idle rpm) to 2,500 rpm and then, the rotating speed of the turbocharger rotor is accelerated from 0 to 100,000 rpm. From those experiments, the comparison between the performances of the air foil bearing and floating ring bearing is conducted and the results show that the air foil bearing has less power loss, maximum 770 watt, than the floating ring bearing, maximum 5,110 watt. This result verifies that the air foil bearing is more efficient and able to output more power under the same condition of the input power.

Effects of the Slopes of the Rotational Axis and Bearing Preloads on the Natural Frequencies and Onset Speed of the Instability of a Rotor Supported on Gas Foil Bearings (가스 포일 베어링으로 지지된 고속 회전체의 경사각과 베어링의 기계적 예압이 고유 진동수와 불안정성 발생 속도에 미치는 영향)

  • Park, Moon Sung;Lee, Jong Sung;Kim, Tae Ho
    • Tribology and Lubricants
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    • v.30 no.3
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    • pp.131-138
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    • 2014
  • This study investigates the effects of the slopes of the rotational axis and bearing preloads on the natural frequencies and onset speeds of the instability of a rotor supported on gas foil bearings (GFBs). The predictive model for the rotating system consists of a rigid rotor supported on two gas foil journal bearings (GFJBs) and a pair of gas foil thrust bearings (GFTBs). Each GFJB supports approximately half the rotor weight. As the slope of the rotational axis increases from $0^{\circ}$(horizontal rotor operation) to $90^{\circ}$(vertical rotor operation), the applied load on the GFJB owing to the rotor weight decreases. The predictions show that the natural frequency and onset speed of instability decrease significantly with an increase in the slope of the rotational axis. In a parametric study, the nominal radial clearance and preload for the GFJB were changed. In general, a decrease in the nominal radial clearance lead to an increase in the natural frequency and onset speed of instability. For constant assembly clearance, the decrease in the preload changed the natural frequency and onset speed of instability with insignificant improvements in the rotordynamic stability. The present predictions can be used as design guidelines for GFBs for oil-free high-speed rotating machinery with improved rotordynamic performance.

Performance Predictions of Gas Foil Thrust Bearings with Turbulent Flow (난류 유동을 갖는 가스 포일 스러스트 베어링의 성능 예측)

  • Mun, Jin Hyeok;Kim, TaeHo
    • Tribology and Lubricants
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    • v.35 no.5
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    • pp.300-309
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    • 2019
  • Gas foil thrust bearings (GFTBs) support axial loads in oil-free, high speed rotating machinery using air or gas as a lubricant. Due to the inherent low viscosity of the lubricant, GFTBs often have super-laminar flows in the film region at operating conditions with high Reynolds numbers. This paper develops a mathematical model of a GFTB with turbulent flows and validates the model predictions against those from the literature. The pressure distribution, film thickness distribution, load carrying capacity, and power loss are predicted for both laminar and turbulent flow models and compared with each other. Predictions for an air lubricant show that the GFTB has high Reynolds numbers at the leading edge where the film thickness is large and relatively low Reynolds numbers at the trailing edge. The predicted load capacity and power loss for the turbulent flow model show little difference from those for the laminar flow model even at the highest speed of 100 krpm, because the Reynolds numbers are smaller than the critical Reynolds number. On the other hand, refrigerant (R-134a) lubricant, which has a higher density than air, had significant differences due to high Reynolds numbers in the film region, in particular, near the leading and outer edges. The predicted load capacity and power loss for the turbulent flow model are 2.1 and 2.3 times larger, respectively, than those for the laminar flow model, thus implying that the turbulent flow greatly affects the performance of the GFTB.

Development of Test Facility for Micro Gas Turbine (마이크로 가스터빈 시험 장치 개발)

  • Lim, Hyung-Soo;Choi, Bum-Seog;Park, Moo-Ryong;Hwang, Soon-Chan;Park, Jun-Young;Seo, Jeongmin;Bang, Je-Sung;Lim, Young-Chul;Oh, In-Kyun;Kim, Byung Ok;Cho, Ju Hyeong
    • The KSFM Journal of Fluid Machinery
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    • v.18 no.5
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    • pp.42-48
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    • 2015
  • To improve the core technology of the micro gas turbine, the performance test facility was developed. This paper is focusing on the explanation of the characteristics of micro gas turbine and its assist devices. Major part of micro gas turbine were radial type of compressor, annular type of combustor, radial type of turbine, thrust foil bearing, radial foil bearing and generator. The assist devices were consist of exhaust duct, inverter, data acquisition system, load bank and test cell. Before building up the test facility, the component test was previously conducted to confirm the component performance. After the test facility was prepared, the motoring test was conducted to investigate the rotor dynamic characteristics of the micro gas turbine. Also, the part load performance test was performed. With a developed micro gas turbine test facility, the improved core technology about the micro gas turbine can be suggested to the related industries.