Numerical study of probe parameters on performance of a transonic axial compressor

Islam, Ashraful; Ma, Hongwei

doi:10.1371/journal.pone.0245711

Cited by 5 publications

(2 citation statements)

References 27 publications

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“…They reported a reduction in efficiency due to the poorly produced shock front for off-design conditions. In a more recent work, Islam and Ma [19] investigated numerically the best locations of probes to reduce the effect on compressor performance during experimental measurements.…”

Section: Introductionmentioning

confidence: 99%

Computational Prediction of the Performance Map of a Transonic Axial Flow Compressor

Idres

Azmi

2022

CFDL

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Aviation fuel efficiency is an important target for aviation industry. Aircraft engine compression ratio is a key factor to improve fuel consumption. Compression ratio can be increased using transonic compressor. In this study, performance prediction of a transonic axial compressor at design and off-design operating conditions is investigated numerically using ANSYS-CFX software. The compressor is NASA Rotor 37. Firstly, the performance at design point is predicted, where mesh independence study is performed to determine suitable mesh size. Three-dimensional flow details for meridional plane, blade-to-blade plane and airfoil surface are explored. The design point study successfully captured flow features such as shock waves and flow separation regions. When compared with experimental data, the predicted compressor pressure ratio deviation error is less than 5%. 3D flow details show that shock wave strength increases from hub to tip. The shock wave moves backward as we move from hub to tip indicating that the flow separation covers lesser portion of the blade. Secondly, off-design performance is predicted for various rotational speeds. A simple procedure is utilized to predict surge and choke limits. The predicted compressor map is compared with experimental data and it shows overall root mean square error less than 5%. The success of the method developed in this research make it a viable method to be used in the design phase of transonic compressors to evaluate the effect of design modifications for both design and off-design operating conditions.

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Section: Introductionmentioning

confidence: 99%

Computational Prediction of the Performance Map of a Transonic Axial Flow Compressor

Idres

Azmi

2022

CFDL

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“…For numerical simulations, the quantity and quality of computational grids play a great role in solutions, so the verification of grid independence is essential. [18][19][20] When tip clearance flows are involved, grids within the clearance should be paid special attention to. As unsteady simulations are commonly conducted to simulate flows such as fluctuation of leakage flow, rotating instability, 21 and flow distortion, 22 the setting of time step must meet the requirements of independence and capturing unsteady features.…”

Section: Introductionmentioning

confidence: 99%

Some effects of non-axisymmetric tip clearance layout on axial compressor aerodynamics

Zhang

Zhuang

Teng

et al. 2021

Proceedings of the Institution of Mechanical Engineers, Part A:

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A steady and unsteady numerical research is carried out to explore some effects of a specific non-axisymmetric tip clearance layout on the overall performance and stability of an axial compressor stage. For a 4-stage low-speed research compressor (LSRC) in Shanghai Jiao Tong University (SJTU), one-eighth annulus of the inlet guide vane and the first stage rotor was modeled for this study. After the validation for the uniform tip clearance case, a specific non-axisymmetric tip clearance layout is chosen from several random cases generated by the Gaussian Probabilistic Density Function method. Unsteady time-averaged results at the near stall condition show that the chosen non-axisymmetric layout can improve the isentropic efficiency by 1.3% and extend the stall margin by 4%. Detailed analyses on flow fields are carried out to interpret the performance improvement. Due to the circumferential layout of clearance sizes, the inlet mass flow and incidence are redistributed in both the radial and circumferential directions. It leads to blade loading and tip leakage flow varying with the tip clearance size. The quantification of blockage manifests that the blockage arising from the tip leakage flow is significantly alleviated in the non-axisymmetric layout, which leads to improvements in overall performance and stall margin. Transient flow fields at the rotor tip are also analyzed at the near stall condition. For the non-axisymmetric layout, low-momentum regions originating from larger clearance sizes oscillate and develop downstream in one blade passage period.

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Study on the influence of pneumatic probe on the wake flow field of transonic turbine cascade

Zhang,

Ma,

Xiao

et al. 2024

Acta Mech. Sin.

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Numerical study of probe parameters on performance of a transonic axial compressor

Cited by 5 publications

References 27 publications

Computational Prediction of the Performance Map of a Transonic Axial Flow Compressor

Computational Prediction of the Performance Map of a Transonic Axial Flow Compressor

Some effects of non-axisymmetric tip clearance layout on axial compressor aerodynamics

Study on the influence of pneumatic probe on the wake flow field of transonic turbine cascade

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