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An axisymmetric characteristic model for enhancing prediction of centrifugal compressor characteristics

Chinese Journal of Aeronautics 2024年第4期37卷 203-215页

作者： Peng REN Xiangjun FANG Zeyu JIAO Ying HAN School of Energy and Power Engineering Beihang UniversityBeijing 100191China Guangdong Key Laboratory of Modern Control Technology Institute of Intelligent ManufacturingGuangdong Academy of SciencesGuangzhou 510070China

Rapid and accurate determination of compressor characteristic maps is essential for the initial design of centrifugal compressors in aircraft power systems. The accuracy of existing methodologies, which rely on combinations of loss models, varies significantly depending on the compressor's geometry and operational range. This variance necessitates substantial experimental or Computational Fluid Dynamics(CFD) data for coefficient calibration. To address this challenge, this study presents an axisymmetric characteristic model for compressor performance assessment. This model incorporates the factors of blade angle, meridional passage area, and the radial deflection angle of meridional streamlines of the compressor. These factors are derived from fundamental aerodynamic equations encompassing mass, momentum, and energy conservation of the compressor. In contrast to conventional one-dimensional approaches, the proposed method reduces the number of loss coefficients and more effectively accounts for the impact of geometric alterations on centrifugal compressor properties. Furthermore, the model reduces dependence on experimental and CFD data. Efficacy of the model is validated using experimental data from four distinct types of centrifugal compressors. Correlation analysis reveals that the model's coefficients can be expressed as functions of the ratio of the Reynolds number to the impeller tip speed. This ratio serves as a characteristic parameter for the design and optimization of centrifugal compressors. Consequently, the proposed method offers an efficient and accurate means for the quick computation of centrifugal compressor characteristics. This is of great significance for improving the efficiency of centrifugal compressors and reducing energy consumption.

关键词： centrifugal compressor Positive problem Characteristic prediction Aerodynamic characteristic Axisymmetric model

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Flow Loss Mechanism in a Supercritical Carbon Dioxide centrifugal compressor at Low Flow Rate Conditions

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Journal of Thermal Science 2024年第1期33卷 114-125页

作者： YANG Zimu JIANG Hongsheng ZHUGE Weilin CAI Ruikai YANG Mingyang CHEN Haoxiang QIAN Yuping ZHANG Yangjun State Key Laboratory of Automotive Safety and Energy Tsinghua UniversityBeijing 100084China School of Mechanical Engineering Shanghai Jiao Tong UniversityShanghai 200240China

With the advantages of high efficiency and compact structure,supercritical carbon dioxide(sC02)Brayton cycles have bright prospects for development in energy conversion *** one of the core components of the power cycle,the centrifugal compressor tends to operate near the critical point(304.13 K,7.3773 MPa).Normally,the compressor efficiency increases as the inlet temperature *** the inlet temperature is close to the critical point,the density increases sharply as the temperature decreases,which results in quickly decreasing of volume flow rate and efficiency *** flow loss mechanism of the sCO_(2) compressor operating at low flow rate is studied in this *** fluid dynamics(CFD) simulations for sCO_(2)compressor were carried out at various inlet temperatures and various mass flow *** the sCO_(2)compressor operates at low volume flow rate,the flow loss is generated mainly on the suction side near the trailing edge of the *** flow loss is related to the counterclockwise vortexes generated on the suction side of the main *** vortexes are caused by the flow separation in the downstream region of the impeller passage,which is different from air compressors operating at low flow *** reason for this flow separation is that the effect of Coriolis force is especially severe for the sCO_(2) fluid,compared to the viscous force and inertial *** lower flow rates,with the stronger effect of Coriolis force,the direction of relative flow velocity deviates from the direction of radius,resulting in its lower radial *** lower radial relative flow velocity leads to severe flow separation on the suction side near the trailing edge of the main blade.

关键词： supercritical CO_(2) centrifugal compressor flow loss mechanism Coriolis force

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Stall Evolution Mechanism of a centrifugal compressor with a Wide-Long Vaneless Diffuser

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Journal of Thermal Science 2024年第3期33卷 899-913页

作者： ZHANG Lei KANG Jiacheng LANG Jinhua AN Guangyao ZHANG Qian WANG Longyao WANG Qifang Department of Power Engineering North China Electric Power UniversityBaoding071003China Hebei Key Laboratory of Low Carbon and High Efficiency Power Generation Technology North China Electric Power UniversityBaoding071003China

The rotating stall mechanism is of high importance for the stability of centrifugal compressors and thermal power *** majority of research concerning this topic has concentrated on the initial stall ***,the evolution of stall cells in wide-long diffusers has not been comprehensively *** this paper,the causes of rotating stall in the wide-long diffuser and the three-dimensional evolution mechanism of stall cells during the stall process were thoroughly *** the stall induction phase,an annulus vortex structure was found in the reverse-flow zone near the hub side of the diffuser outlet,which was the initial form of stall *** whole evolution process of stall cells was divided into three phases as the flow rate *** the initial stall phase,the dynamic equilibrium was built under effects of the impeller wake and the adverse pressure *** a result,the number of stall cells was kept at seven and the size of stall cells remained *** the transition phase,the flow in the diffuser became *** cells extended to the impeller outlet,and the effect of the wake flow was strengthened *** cells started integrating and separating *** a result,the number and propagation speed of stall cells varied periodically at a constant mass flow *** the deep stall phase,the size of stall cells remained unchanged,and the number of stall cells kept at *** study has important practical guidance and engineering value for the high-efficiency design and safe operation of centrifugal compressors.

关键词： centrifugal compressor wide-long vaneless diffuser stall evolution mechanism wake flow

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Radial Forces in a centrifugal compressor; Experimental Investigation by Using Magnetic Bearings and Static Pressure Distribution

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Journal of Thermal Science 2005年第1期14卷 1-8页

作者： Arttu REUNANEN Jaakko LARJOLA Department of Energy and Environmental Technology Lappeenranta University of Technology LappeenrantaFinlandDepartment of Energy and Environmental Technology Lappeenranta University of TechnologyLappeenrantaFinland

The volute of a centrifugal compressor causes a non-uniform pressure distribution which leads to a radial force on the impeller. This force was measured using magnetic bearings. In addition, the radial force was estimated using the static pressure distribution measured at the impeller outlet. The impeller force was found to be the highest at choke, the lowest at the design flow and moderate at stall. The radial force determined from the pressure measurements was only slightly different from the force obtained from the bearing measurements. The rotational speed was seen to affect the force to some extent.

关键词： centrifugal compressor aerodynamic force radial force volute.

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Measurement and Numerical Simulation of a Small centrifugal compressor Characteristics at Small or Negative Flow Rate

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Journal of Thermal Science 2017年第2期26卷 107-112页

作者： Kaname Tsukamoto Mizuki Okada Yuzo Inokuchi Nobuhiko Yamasaki Akihiro Yamagata Kyushu University Motooka 744819-0395FukuokaJapan IHI Corporation Shin-Nakahara 1235-8501YokohamaJapan

For centrifugal compressors used in automotive turbochargers, the extension of the surge margin is demanded because of lower engine speed. In order to estimate the surge line exactly, it is required to acquire the compressor characteristics at small or negative flow rate. In this paper, measurement and numerical simulation of the characteristics at small or negative flow rate are carried out. In the measurement, an experimental facility with a valve immediately downstream of the compressor is used to suppress the surge. In the numerical work, a new boundary condition that specifies mass flow rate at the outlet boundary is used to simulate the characteristics around the zero flow rate region. Furthermore, flow field analyses at small or negative flow rate are performed with the numerical results. The separated and re-circulated flow fields are investigated by visualization to identify the origin of losses.

关键词： centrifugal compressor turbocharger measurement CFD RANS surge small flow negative flow

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Experimental and Computational Analysis of the Unstable Flow Structure in a centrifugal compressor with a Vaneless Diffuse

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Chinese Journal of Mechanical Engineering 2019年第4期32卷 127-139页

作者： Xiang Xue Tong Wang Gas Turbine Research Institute Shanghai Jiao Tong University

The unstable flow phenomena in compressors, such as stall and surge, are closely related to the e ciency and the operating region. It is indispensable to capture the unstable flow structure in compressors and understand the mechanism of flow instability at low flow rates. Cooperated with the manufacturer, an industrial centrifugal compressor with a vaneless di user is tested by its performance test rig and our multi-phase dynamic measurement system. Many dynamic pressure transducers are circumferentially mounted on the casing surface at seven radial locations, spanning the impeller region and the di user inlet region. The pressure fields from the design condition to surge are measured in details. Based on the multi-phase dynamic signals, the original location of stall occurring can be determined. Meanwhile, the information of the unstable flow structure is obtained, such as the circumferential mode and the propagating speed of stall cells. To get more details of the vortex structure, an unsteady simulation of this tested compressor is carried out. The computational result is well matched with the experimental result and further illustrates how the unstable flow structure in the impeller region gradually a ects the stability of the total machine at low flow rates. The dynamic mode decomposition(DMD) method is applied to get the specific flow pattern corresponding to the stall frequency. Both experimental and computational analysis show that the flow structure at a particular radial location in the impeller region has a great impact on the stall and surge. Some di erences between the computational and experimental result are also discussed. Through these two main analytical methods, an insight into the unstable flow structure in an industrial compressor is gained. The result also plays a crucial role in the guidance of the compressor stabilization techniques.

关键词： Unstable flow Vortex structure centrifugal compressor Vaneless di user

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The Influence of Wedge Diffuser Blade Number and Divergence Angle on the Performance of a High Pressure Ratio centrifugal compressor

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Journal of Thermal Science 2018年第1期27卷 17-24页

作者： WANG Yi HAN Ge LU Xingen ZHU Junqiang School of Aeronautics and Astronautics Central South UniversityChangsha 410083China Institute of Engineering Thermophysics Chinese Academy of SciencesBeijing 100190China

Wedge diffuser is widely used in centrifugal compressors due to its high performance and compact size. This paper is aimed to research the influence of wedge diffuser blade number and divergence angle on centrifugal compressor performance. The impact of wedge diffuser blade number on compressor stage performance is investigated, and then the wedge diffusers with different divergence angle are studied by varying diffuser wedge angle and blade number simultaneously. It is found that wedge diffuser with 27 blades could have about 0.8% higher adiabatic efficiency and 0.14 higher total pressure ratio than the wedge diffuser with 19 blades and the best compressor performance is achieved when diffuser divergence angle is 8.3°.These results could give some advices on centrifugal compressor design.

关键词： Wedge diffuser Blade number Diffuser angle High pressure ratio centrifugal compressor

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Design and Prototyping of Micro centrifugal compressor for Ultra Micro Gas Turbine

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Journal of Thermal Science 2005年第4期14卷 308-313页

作者： Shimpei MIZUKI Toshiyuki HIRANO Yoshiyuki KOIZUMI Gaku MINORIKAWA Hoshio TSUJITA Mitsuo IWAHARA Ronglei GU Yutaka OHTA Eisuke OUTA Department of Mechanical Engineering Hosei University Japan Graduate School of Engineering Mechanical Engineering Hosei University 7-2 Kajinocho 3 chomeKoganei-shi Tokyo 184-8584 Japan Department of Mechanical Engineering Waseda University

In order to establish the design methodology of an ultra micro centrifugal compressor, which is the most important component of an ultra micro gas turbine unit, a 10 times size of the final target compressor （impeller outer diameter 40 mm, corrected rotational speed 220,000 r/min） was designed. The problems to be solved for downsizing were examined and a 2-dimensional impeller was chosen as the first model due to its productivity. The conventional 1D prediction method and CFD were used. The prototyped compressor was tested by using cold air at the reduced speed of 110,000 r/min. Following to the 10 times model, a 5 times size of the final target model having fully 3-dimensional shape （impeller outer diameter 20mm, corrected rotational speed 500,000 r/min） was designed and tested by using hot gas at the reduced speed of 250,000 r/min.

关键词： centrifugal compressor performance characteristics 3-dimensional impeller.

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Study on Rotational Frequency Noise in a centrifugal compressor for Automobile Turbochargers

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Journal of Thermal Science 2014年第1期23卷 53-59页

作者： Daichi Wakaki Yuta Sakuka Nobuhiko Yamasaki Akihiro Yamagata Department of Aeronautics and Astronautics Kyushu University Products Development Center IHI Corporation

The rotational frequency noise(also known as the pulsation noise) due to the mistuning of impeller blade rows introduced at the manufacturing stage of the impellers is observed in the small-sized centrifugal compressor for automobile turbochargers. The present paper addresses the elucidation of the generating mechanism and parameter dependency such as the kind and degree of mistuning. In order to analyze numerically the rotational frequency noise due to mistuning, the unsteady computational fluid dynamics(CFD) of the whole compressor including volute is executed, and the resultant time history of the pressure is fed into the spectral analysis.

关键词： centrifugal compressor Impeller Diffuser Volute Pulsation noise Mistuning

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Design and Optimization of a Single Stage centrifugal compressor for a Solar Dish-Brayton System

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Journal of Thermal Science 2013年第5期22卷 404-412页

作者： Yongsheng Wang Kai Wang Zhiting Tong Feng Lin Chaoqun Nie Abraham Engeda Key Laboratory of Advanced Energy and Power Chinese Academy of Sciences Institute of Engineering Thermophysics Chinese Academy of Sciences Graduate University of Chinese Academy of Science Department of Mechanical Engineering Michigan State University

According to the requirements of a solar dish-Brayton system,a centrifugal compressor stage with a minimum total pressure ratio of 5,an adiabatic efficiency above 75% and a surge margin more than 12% needs to be designed.A single stage,which consists of impeller,radial vaned diffuser,90° crossover and two rows of axial stators,was chosen to satisfy this *** achieve the stage performance,an impeller with a 6:1 total pressure ratio and an adiabatic efficiency of 90% was designed and its preliminary geometry came from an in-house one-dimensional *** vaned diffuser was applied downstream of the *** rows of axial stators after 90° crossover were added to guide the flow into axial *** jet-wake flow,shockwave and boundary layer separation coexisted in the impeller-diffuser region,optimization on the radius ratio of radial diffuser vane inlet to impeller exit,diffuser vane inlet blade angle and number of diffuser vanes was carried out at design ***,an optimized centrifugal compressor stage fulfilled the high expectations and presented proper *** simulation showed that at design point the stage adiabatic efficiency was 79.93% and the total pressure ratio was *** surge margin was 15%.The performance map including 80%,90% and 100% design speed was also presented.

关键词： Single Stage centrifugal compressor Design Optimization

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