Numerical Investigation of Rotating Stall Characteristics in a Full-Annulus Transonic Centrifugal Compressor

2020 ◽  
pp. 1-12
Author(s):  
Ali Zamiri ◽  
Minsuk Choi ◽  
Jin Taek Chung
Keyword(s):  
Numerical Investigation ◽  
Centrifugal Compressor ◽  
Rotating Stall ◽  
Transonic Centrifugal Compressor

Unsteady and Three-Dimensional Flow Phenomena in a Transonic Centrifugal Compressor Impeller at Rotating Stall

2009 ◽  
Author(s):  
Kenichiro Iwakiri ◽  
Masato Furukawa ◽  
Seiichi Ibaraki ◽  
Isao Tomita
Keyword(s):  
Centrifugal Compressor ◽  
Wavelet Transforms ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Internal Flow ◽  
Leading Edge ◽  
Rotating Stall ◽  
Detached Eddy Simulation ◽  
Transonic Centrifugal Compressor ◽  
Compressor Impeller

This paper presents a combined experimental and numerical analysis of rotating stall in a transonic centrifugal compressor impeller for automotive turbochargers. Stall characteristics of the compressor were examined by two high-response pressure transducers mounted on the casing wall near the impeller inlet. The pressure traces were analyzed by wavelet transforms to estimate the disturbance waves quantitatively. Three-dimensional unsteady internal flow fields were simulated numerically by Detached Eddy Simulation (DES) coupled LES-RANS approach. The analysis results show good agreements on both compressor performance characteristics and the unsteady flow features at the rotating stall. At stall inception, spiral-type breakdown of the full-blade tip leakage vortex was found out at some passages and the brokendown regions propagated against the impeller rotation. This phenomenon changed with throttling, and tornado-type separation vortex caused by the full-blade leading edge separation dominated the flow field at developed stall condition. It is similar to the flow model of short-length scale rotating stall established in an axial compressor rotor.

Numerical investigation of rotating stall in centrifugal compressor with vaned and vaneless diffuser

2015 ◽  
Vol 24 (4) ◽  
pp. 323-333 ◽  
Author(s):  
Taher Halawa ◽  
Mohamed Alqaradawi ◽  
Mohamed S. Gadala ◽  
Ibrahim Shahin ◽  
Osama Badr
Keyword(s):  
Numerical Investigation ◽  
Centrifugal Compressor ◽  
Rotating Stall ◽  
Vaneless Diffuser

0608 Detached Eddy Simulation of Rotating Stall in a Transonic Centrifugal Compressor with Single Splitter Blades

2010 ◽  
Vol 2010 (0) ◽  
pp. 195-196
Author(s):  
Hisataka FUKUSHIMA ◽  
Yusuke TAMAGAWA ◽  
Kazutoyo YAMADA ◽  
Masato FURUKAWA ◽  
Seiichi IBARAKI
Keyword(s):  
Centrifugal Compressor ◽  
Rotating Stall ◽  
Detached Eddy Simulation ◽  
Eddy Simulation ◽  
Transonic Centrifugal Compressor

The Role of Tip Leakage Vortex Breakdown in Flow Fields and Aerodynamic Characteristics of Transonic Centrifugal Compressor Impellers

2011 ◽  
Author(s):  
Kazutoyo Yamada ◽  
Masato Furukawa ◽  
Hisataka Fukushima ◽  
Seiichi Ibaraki ◽  
Isao Tomita
Keyword(s):  
Flow Rate ◽  
Centrifugal Compressor ◽  
Vortex Breakdown ◽  
Aerodynamic Characteristics ◽  
Flow Fields ◽  
Rotating Stall ◽  
Tip Leakage Vortex ◽  
Tip Leakage ◽  
Transonic Centrifugal Compressor ◽  
Compressor Impeller

This paper describes the experimental and numerical investigations on unsteady three-dimensional flow fields in two types of transonic centrifugal compressor impellers with different aerodynamic characteristics. In the experimental results, the frequency spectra of the pressure fluctuations, which were measured with the high-response pressure transducers mounted on the casing wall just upstream of the impeller, turned out to be quite different between the compressor impellers at stall condition. The simulation results also showed different stall pattern for each compressor impeller. In the compressor impeller with a better performance at off-design condition, the stall cell was never formed despite decreasing flow rate and instead all the passages were covered with a reverse flow near the tip, where the vortex breakdown happened in the tip leakage vortex of full blade and led to the unsteadiness in the impeller. The vortex breakdown happened in all the passages prior to the stall and generated a blockage near the tip. This means that even with the advent of rotating stall the flow could not return to a normal undistorted condition in unstalled region, because all the passages are already occupied by the blockage due to the vortex breakdown. As a result, the rotating stall cell could not appear in the impeller. In the other compressor impeller, the rotating stall cell was formed at stall inception without the vortex breakdown in the tip leakage vortex of full blade, and developed with decreased flow rate.

Numerical Investigation of the Unsteady Flow Inside a Centrifugal Compressor Stage With Pipe Diffuser

2013 ◽  
Author(s):  
Daniel R. Grates ◽  
Peter Jeschke ◽  
Reinhard Niehuis
Keyword(s):  
Experimental Data ◽  
Unsteady Flow ◽  
Numerical Investigation ◽  
Centrifugal Compressor ◽  
Measurement Techniques ◽  
Navier Stokes ◽  
Compressor Stage ◽  
Centrifugal Compressor Stage ◽  
Transonic Centrifugal Compressor ◽  
The Subject

The subject of this paper is the investigation of unsteady flow inside a transonic centrifugal compressor stage with pipe-diffuser by utilizing unsteady 3D Navier-Stokes simulations (unsteady 3D URANS). The CFD results obtained are compared with detailed experimental data gathered using various steady and unsteady measurement techniques. The basic phenomena and mechanisms of the complex and highly unsteady flow inside the compressor with pipe-diffuser are presented and analyzed in detail.

Numerical investigation of the diffuser throat length effect on a transonic centrifugal compressor

2021 ◽  
pp. 095440622110401
Author(s):  
Qingkuo Li ◽  
Yingjie Zhang ◽  
Yi Wang ◽  
Ge Han ◽  
Yanfeng Zhang ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Centrifugal Compressor ◽  
Flow Direction ◽  
Divergence Angle ◽  
Centrifugal Compressors ◽  
Vaned Diffuser ◽  
Stall Margin ◽  
Transonic Centrifugal Compressor ◽  
Fluid Pressurization ◽  
Large Flow

Vaned diffuser inlet flow uniform is challenging when the impeller is throttled to stall. In this study, we extend the stable operating range of the compressor by improving the uniform flow of the diffuser inlet. First, a numerical investigation of a transonic centrifugal compressor with a vaned diffuser is presented and compared against test data. Then, a new diffuser parameterization method is pro- posed, and the throat feature of a pipe diffuser is successfully applied to parameterized vane diffusers. The influence of the throat length and divergence angle of the diffuser on the performance of the centrifugal compressor is studied via steady and non-linear harmonic simulations. Throat length delays the time of fluid pressurization and accommodates large flow instabilities from upstream—this widens the stall margin but increases mixing loss. Divergence angle affects compressor performance. Stage peak efficiency increases by about 0.58% as the divergence angle increases from 3.79° to 5.79° but drops to about 2.46% as the divergence angle further increases from 5.79° to 11.79°. This is because the boundary layers in the diffuser channel thicken with increasing divergence angle; additionally, the fluid near the hub-pressure side first becomes unstable, then flow separation occurs along the flow direction, which results in a large flow loss. Detailed performance maps of centrifugal compressors with different throat lengths and divergence angles are given to provide a reference for designing transonic centrifugal compressors.

Evolution of Reverse Flow in a Transonic Centrifugal Compressor at Near-Surge

2017 ◽  
Author(s):  
Kazutoyo Yamada ◽  
Masato Furukawa ◽  
Hiromitsu Arai ◽  
Dai Kanzaki
Keyword(s):  
Centrifugal Compressor ◽  
Reverse Flow ◽  
High Reliability ◽  
Pressure Rise ◽  
Flow Region ◽  
Flow Fields ◽  
Rotating Stall ◽  
Centrifugal Compressors ◽  
Transonic Centrifugal Compressor ◽  
Flow Phenomena

In process centrifugal compressors used in various types of plants, the compressor is the heart of a plant, and it requires high reliability. Therefore, prediction of the surge is important for centrifugal compressors. There have been numerous researches on the surge: study on improvement of surge margin, and study on the rotating stall, which is recognized as a precursor to surge, in impeller or diffuser of the compressor. However, the researches have not focused on the surge inception flow phenomena, namely detailed flow mechanism leading to the surge, although understanding of such flow phenomena is important for prediction of the surge. The paper describes in detail unsteady flow fields in a transonic centrifugal compressor at near-surge conditions. The flow fields have been investigated by detached eddy simulations (DES) using 400 million grid points. The simulation results show that the huge reverse flow region occupies the flow field near the shroud in the impeller at off-design condition, triggered by the blade stall at the tip of impeller full-blade, and it drastically develops at near-surge. It is also found that the rotating disturbance with reversed flow appears in the diffuser near the endwall at around peak pressure-rise point, and it eventually evolves into the rotating stall cell with a large reverse flow, blocking the flow inside the diffuser at near-surge.

C15 Wavelet Analysis of Pressure Fluctuation in a Transonic Centrifugal Compressor at Rotating Stall Conditions

2008 ◽  
Vol 2008.61 (0) ◽  
pp. 83-84
Author(s):  
Hiroyuki Takafuji ◽  
Ken-ichiro Iwakiri ◽  
Ryota Suzuki ◽  
Masato Furukawa ◽  
Seiichi Ibaraki ◽  
...  
Keyword(s):  
Wavelet Analysis ◽  
Centrifugal Compressor ◽  
Pressure Fluctuation ◽  
Rotating Stall ◽  
Transonic Centrifugal Compressor
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