Numerical Study on the Effect of Single Shallow Circumferential Groove Casing Treatment on the Flow Field and the Stability of a Transonic Compressor

Mirzabozorg, Mohsen Agha Seyed; Bazazzadeh, Mehrdad; Hamzezade, Morteza

doi:10.18869/acadpub.jafm.73.238.26480

Cited by 8 publications

(2 citation statements)

References 24 publications

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“…The k-ω turbulent SST model is used with a highresolution approach to advection. The same turbulence model was used previously by Mirzabozorg et al (2016). They achieved optimum results in their work.…”

Section: Numerical Solver Governing Equations and Boundary Conditionsmentioning

confidence: 85%

Computational Analysis on the Performance of Centrifugal Compressor with Tapered Wall and Rotating Tapered Wall Vaneless Diffuser

Niveditha¹,

Prasad²

2021

JAFM

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Computational analysis is performed on a centrifugal compressor fitted with tapered vaneless diffuser in order to increase the rate of diffusion. The main parameter involved in the present study is the wall taper angle of the diffuser, which is varied from 1° to 6° in the interval of 1°. Simulations are performed for the stationary as well as rotating diffuser at a speed of 79,000rpm, by using ANSYS CFX 17.2. By considering the geometry with stationary parallel wall diffuser as the base case, the performance enhancement in the characteristics such as static pressure recovery coefficient, stagnation pressure loss coefficient, isentropic efficiency, energy coefficient and torque coefficient are reported. The flow features in the compressor having various diffuser geometries are studied with the help of static pressure, radial velocity, static entropy, and contours of velocity streamlines at the design point. Of all the cases of stationary tapered diffusers, the diffuser with 3° taper angle showed optimum performance: the increase in isentropic efficiency (η) is by 1.5%, the increase in static pressure recovery coefficient (CP) is by about 9% and the decrease in stagnation pressure loss coefficient (CPOL) by 10.7%. On the other hand, it was found that in the case of rotating diffuser optimum performance: an increase of about 40% in CP and decrease of about 32% in CP0L occurred for a taper angle of 6°. However, its efficiency decreased by 2.9% with rotating diffuser in comparison with the base case, due to increased energy losses.

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Section: Numerical Solver Governing Equations and Boundary Conditionsmentioning

confidence: 85%

Computational Analysis on the Performance of Centrifugal Compressor with Tapered Wall and Rotating Tapered Wall Vaneless Diffuser

Niveditha¹,

Prasad²

2021

JAFM

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“…The results showed an optimum location of the circumferential groove near the blade leading edge (but not above), and that deeper grooves present better performance than shallow grooves. Mirzabozorg et al [26] analyzed the width of the circumferential grooves. If the width of the groove is large, it can adversely affect the compressor stall margin.…”

Section: Smmentioning

confidence: 99%

An Evaluation of Passive Wall Treatment With Circumferential Grooves at the Casing of the First and Second Blade Rotor Rows of a High-performance Multi-stage Axial Compressor

Diaz,

Tomita,

Bringhenti

et al. 2023

Preprint

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The internal losses in the tip clearance region strongly influence the compressor performance and its operational range. Previous research proved that passive wall treatments with circumferential grooves in axial compressors effectively increase the compressor stall margin. The vortex generated inside the circumferential grooves create a resistance to the flow that leaks in the tip clearance region of the compressor. However, most works found in the literature on circumferential grooves in axial compressors deal only with high-performance single-stage axial compressors. Therefore, there is a need to investigate and analyze the behavior of circumferential grooves in a multi-stage environment. In the present work, a passive wall treatment with circumferential grooves was implemented in a multi-stage axial compressor. Different configurations of circumferential grooves were created at the casing of the first and second rotor rows used in a four-stage axial flow compressor. Numerical simulations were performed to evaluate the influence of the circumferential grooves on the performance of a multi-stage axial compressor. The results obtained after the simulations for the different circumferential groove configurations were compared with the results obtained for the compressor without casing treatment (smooth wall) for different rotational speeds. Furthermore, the complete compressor map characteristics were simulated for the different casing treatment configurations, and the results were compared with the compressor characteristics of the smooth wall case. The passive wall treatment with circumferential grooves produced changes in the multi-stage axial compressor flow field, especially in the tip clearance region, improving the compressor stability mainly for part load speeds.

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Improvements of performance and stability of a single-stage transonic axial compressor using a combined flow control approach

Wang

Huang

2019

Aerospace Science and Technology

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Numerical Study on the Effect of Single Shallow Circumferential Groove Casing Treatment on the Flow Field and the Stability of a Transonic Compressor

Cited by 8 publications

References 24 publications

Computational Analysis on the Performance of Centrifugal Compressor with Tapered Wall and Rotating Tapered Wall Vaneless Diffuser

Computational Analysis on the Performance of Centrifugal Compressor with Tapered Wall and Rotating Tapered Wall Vaneless Diffuser

An Evaluation of Passive Wall Treatment With Circumferential Grooves at the Casing of the First and Second Blade Rotor Rows of a High-performance Multi-stage Axial Compressor

Improvements of performance and stability of a single-stage transonic axial compressor using a combined flow control approach

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