Unsteady wall pressure measurement in a one-and-a-half stage axial transonic compressor during stall inception

Biela, Christoph; Brandstetter, Christoph; Schiffer, Heinz-Peter; Heinichen, Frank

doi:10.1177/0957650913495385

Cited by 9 publications

(3 citation statements)

References 22 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Yamada et al 14 suggested that the periodic breakdown of the TLV resulted in self-sustained flow oscillation in the tip leakage flow field. Biela et al 15 suggested that the unsteadiness of the flow in the tip region was mainly caused by TLV oscillation with the frequency of around 0.5 BPF. Du et al 16 suggested that the momentum ratio between the main flow and the TLF can be one of the factors that dominate the self-induced unsteadiness in the tip region.…”

Section: Introductionmentioning

confidence: 99%

Investigation of tip leakage flow unsteadiness and rotating instability in a centrifugal compressor impeller

Wang

Yang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part D:

View full text Add to dashboard Cite

A phenomenon called rotating instability was rarely reported in a centrifugal compressor, although some associated discussions can be found in axial compressors. This paper presents a numerical investigation on the unsteadiness of the tip leakage flow and rotating instability in an isolated centrifugal compressor impeller. A three-dimensional, unsteady full annuls simulation is performed under three different operating conditions. The tip leakage flow unsteadiness at the impeller inlet and inside the impeller passage is detected by the pressure fluctuation. During the throttling process, the temporal and spatial propagation characteristic of the tip leakage flow unsteadiness under the near stall operating condition is revealed based on the wavelet analysis, Fourier transform, and dynamic mode decomposition. Furthermore, the relationship between the tip leakage flow unsteadiness and the rotating instability is also discussed. The results show that the pressure fluctuation mainly concentrates in the tip region at the near stall operating condition, which indicates the occurrence and circumferential propagation of tip leakage flow unsteadiness. The circumferential propagation of the tip leakage flow unsteadiness induces a significant circumferential rotating pressure wave with a wave number of 9 and approximately 48.2% of the rotational speed of the impeller. The characteristic frequency of the tip leakage flow unsteadiness agrees well with the dominant mode frequency of rotating instability. Therefore, the tip leakage flow unsteadiness is assumed to be responsible for the rotating instability. During the throttling process, the formation and development of the rotating instability at near stall operating condition can be divided into three stages based on signal analysis: prior to rotating instability, generation and development, and rotating instability.

show abstract

Section: Introductionmentioning

confidence: 99%

Investigation of tip leakage flow unsteadiness and rotating instability in a centrifugal compressor impeller

Wang

Yang

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part D:

View full text Add to dashboard Cite

show abstract

“…Through the measurement of pulsation of the axial velocity in a single-stage axial compressor, Mcdougall [12] first discovered the model type stall inception characterized by large-scale disturbance, smaller rotation speed, and lack of specific time and origin of space. In recent years, relevant researches at home and abroad have shown that the adjustment of structural and operating parameters can change complex flow fields in flow passages, affecting the forms of stall inception [13,14]. Bianchi S et al [15] conducted an experimental study on stall inception patterns under different installation angles of rotor blades in a low-speed axial fan.…”

Section: Introductionmentioning

confidence: 99%

Effects of the Second-Stage of Rotor with Single Abnormal Blade Angle on Rotating Stall of a Two-Stage Variable Pitch Axial Fan

Zhang

et al. 2018

Energies

View full text Add to dashboard Cite

It is of great value to study the impact of abnormal blade installation angle on the inducement mechanism of rotating stall to achieve the active control of rotating stall in an axial fan. Based on throttle value function and SST k-ω turbulence model, numerical simulations of the unsteady flow process in stall condition of an axial flow fan with adjustable vanes were carried out, and the influence mechanism of abnormal stagger angle of a single blade in the second stage rotor on induced position and type of stall inception and evolution process of rotating stall were analyzed. The results show that compared with synchronous adjustment of blade angle, the blade with abnormal stagger angle will cause the increase of flow rate at the beginning of stall and make the fan fall into an unstable condition in advance. The existence of blade with abnormal angle does not cause the change of the induced position and type of stall inception and the inducement mechanism of rotating stall, which are the same as the axial fan with normal blade angle. Moreover, the single blade with abnormal deviation angle has important impacts on the 3D unsteady evolution process from stall inception to stall cell formation in two rotors.

show abstract

“…Spikes rotate at 70–80% of the rotor speed, and the time between the first detection of a spike and the formation of a large stall cell is less than five rotor revolutions, much shorter than the time of evolution of the modal-type inception. 7–13…”

Section: Introductionmentioning

confidence: 99%

Experimental investigations on instability evolution in a transonic compressor at different rotor speeds

Pan

Sun

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part C:

View full text Add to dashboard Cite

Experimental investigations are conducted to study the instability evolution in a transonic axial flow compressor at four specific rotor speeds covering both subsonic and transonic operating conditions. Two routes of evolution to final instability are observed in the test compressor: at low rotor speeds, a disturbance in the rotor tip region occurs and then leads to rotating stall, while at high rotor speeds, a low-frequency disturbance in the hub region leads the compressor into instability. Different from stall and surge, this new type of compressor instability at high rotor speed is initiated through the development of a low-frequency axisymmetric disturbance at the hub, and we name it “partial surge”. The frequency of this low-frequency disturbance is approximately the Helmholtz frequency of the system and remains constant during instability inception. Finally, a possible mechanism for the occurrence of different instability evolutions and the formation of partial surge are also discussed.

show abstract

Unsteady wall pressure measurement in a one-and-a-half stage axial transonic compressor during stall inception

Cited by 9 publications

References 22 publications

Investigation of tip leakage flow unsteadiness and rotating instability in a centrifugal compressor impeller

Investigation of tip leakage flow unsteadiness and rotating instability in a centrifugal compressor impeller

Effects of the Second-Stage of Rotor with Single Abnormal Blade Angle on Rotating Stall of a Two-Stage Variable Pitch Axial Fan

Experimental investigations on instability evolution in a transonic compressor at different rotor speeds

Contact Info

Product

Resources

About