Effects of tip clearance size on the performance and tip leakage vortex in dual-rows counter-rotating compressor

Wang, Yangang; Chen, Weixiong; Chen, Wu; Ren, Siyuan

doi:10.1177/0954410014562483

Cited by 36 publications

(32 citation statements)

References 25 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…O4H topology was chosen to model the main flow passage, and butterfly topology was adopted to model the real tip clearance of rotors. Investigation of grid refinement was conducted by Wang et al 24 on the CRAC of current paper, and the results showed that the performance of the compressor keeps almost unchanged if the grid number exceeds to 2.5 Â 10 6 . Considering both accuracies and computational demands, grid number of 2.6 Â 10 6 approximately for the CRAC in the steady simulations and about 1.4 Â 10 6 for the two rotors in the unsteady numerical computations is adopted, respectively.…”

Section: Methodsmentioning

confidence: 95%

A numerical study on the unsteady effect of axial spacing on the performance in a contra-rotating axial compressor

Mao

Liu

2016

Proceedings of the Institution of Mechanical Engineers, Part C:

View full text Add to dashboard Cite

Unsteady numerical simulations are conducted to investigate the unsteady effects of axial spacing on the performance of a contra-rotating axial compressor. The results show that the stage efficiency is dominant by unsteady effects between two rotors at lower axial gap ranges. As the axial spacing is increased, the variation of aerodynamic force is different for the two rotors. As a whole, the oscillation on the pressure surface is much stronger than that on the suction side in rotor1. For rotor2, however, the local maximum amplitude is just located at the blade leading edge, especially near the tip region. Additionally, the maximum amplitude of the pressure fluctuations generally decreases with an increase of axial spacing. The dominating frequency is different for monitors located at different positions and varies with the increasing of axial gaps. As the axial gap is increased, the potential effects decay in the process of propagating. Meanwhile, the incoming wakes are mixed out more sufficiently which would reduce the fluctuations at leading edge of rotor2. Therefore, a proper axial spacing should be chosen in the design process of a contra-rotating axial compressor considering both the performance and structure.

show abstract

Section: Methodsmentioning

confidence: 95%

A numerical study on the unsteady effect of axial spacing on the performance in a contra-rotating axial compressor

Mao

Liu

2016

Proceedings of the Institution of Mechanical Engineers, Part C:

View full text Add to dashboard Cite

show abstract

“…The validation work of the NUMECA FINE-Turbo has also been done by other researchers. Wang, Chen, Wu, and Ren (2014) have shown good agreements of compressor performance maps between the computed results and the experimental data in a counter-rotating axial compressor when using the Spalart-Allmaras model. Lange, Vogeler, Mailach, and Gomez (2013) have shown that the NUMECA FINE-Turbo-computed blade pressure distributions have quite good agreement with the experiment.…”

Section: Cfd Validationsmentioning

confidence: 68%

Using forward end-sweep to reduce transonic cantilevered stator losses to improve compressor performance

Pan

2018

Engineering Applications of Computational Fluid Mechanics

View full text Add to dashboard Cite

The complicated flows in a transonic cantilevered stator would cause serious aerodynamic losses and reducing these losses would contribute much to improving the overall aerodynamic performance of a compressor. The paper conducts an overview study of the potential aerodynamic losses in a transonic cantilevered stator and presents a systematic numerical study for the effects of forward end sweep on reducing aerodynamic losses. A 2-D stator blade is used to throw light upon the physical mechanism of the forward end sweep on reducing the losses. At the casing region, forward end sweep has led to a redistribution of the blade load along the chordwise direction, higher in the front part and lower in the rear part. This result leads to a lower pressure gradient from the 30% chord location to the trailing edge and can be beneficial for the reduction of the corner separation. At the hub region, on one aspect, forward end sweep reduces both the peak Mach number and the size of the high-Ma region of the blade suction surface, thus decreasing the shock loss near the hub. On the other aspect, it also reduces the peak load and the strength of the leakage vortex, therefore alleviating the flow blockages. Simultaneously, the forward end sweep is applied to a commercial and high-performance multistage compressor to further validate its feasibility. When the technique is applied to the transonic first four stator rows, an improvement of adiabatic efficiency is achieved by ∼ 0.85% and the compressor stable operating range is slightly increased. The results suggest that the forward end-swept transonic cantilevered stators have a significant potential for reducing the stator losses. They would provide guidelines to advance the cantilevered stator design and further improve the compressor aerodynamic performance.

show abstract

“…However, changes in these parameters are finally reflected with changes in integral parameters. Therefore, the verification method using integral parameters is widely applied in many researches [21,[24][25][26][27]. To verify the mesh independence, fans with mesh numbers of 3.82, 4.26, 4.65, 5.33 and 5.56 million are simulated in this study, as shown in Table 3.…”

Section: Meshingmentioning

confidence: 99%

Prediction of Performance of a Variable-Pitch Axial Fan with Forward-Skewed Blades

Ye¹,

Fan²,

Zhang³

et al. 2019

Energies

View full text Add to dashboard Cite

For a single-stage variable-pitch axial fan, the aerodynamic performance and through flow with and without blade skewing are examined numerically. Simulated results show that the total pressure rise and efficiency increase by 2.99% and 0.16%, respectively, with the best forward-skewed angle of θ = 3° at the design conditions. At the blade pitch angles of β = 29° and 35°, the total pressure rises and efficiency of the fan with θ = 3.0° under the highest efficiency point change by −0.55%, −0.53% and 1.39%, 2.11%, respectively. At design and off-design conditions, the forward-skewed blades mitigate tip leakage and delay the emergence of separation flow at the blade root, these benefits are higher at the higher blade pitch angle. The θ = 3.0° forward skew effectively raises the stage performance of the impeller and guide vanes.

show abstract

Effects of tip clearance size on the performance and tip leakage vortex in dual-rows counter-rotating compressor

Cited by 36 publications

References 25 publications

A numerical study on the unsteady effect of axial spacing on the performance in a contra-rotating axial compressor

A numerical study on the unsteady effect of axial spacing on the performance in a contra-rotating axial compressor

Using forward end-sweep to reduce transonic cantilevered stator losses to improve compressor performance

Prediction of Performance of a Variable-Pitch Axial Fan with Forward-Skewed Blades

Contact Info

Product

Resources

About