Investigation of an Inversely Designed Centrifugal Compressor Stage—Part I: Design and Numerical Verification

Zangeneh, Mehrdad; Schleer, Matthias; Plöger, Felix; Hong, S. S.; Roduner, Christian; Ribi, Beat; Abhari, Reza S.

doi:10.1115/1.1645868

Cited by 34 publications

(21 citation statements)

References 12 publications

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“…The streamline curvature method plays an important role in the preliminary design phase of radial [1][2][3][4] and axial turbomachinery applications 5 because of its simple and compact equations, definite physical meanings, and straightforward solving algorithm. In the method, the velocity profile on the stream surface is specified by solving the S2m stream surface velocity gradient equation.…”

Section: Introductionmentioning

confidence: 99%

A new finite difference method to solve the velocity gradient equation in streamline curvature method

Gong

Zhang

2016

Advances in Mechanical Engineering

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For the inverse proposition design of a three-dimensional centrifugal impeller using the streamline curvature method, the cubic spline curve fitting method is extensively used to solve the velocity gradient equation. Given the deficiency in stability with the cubic spline curve fitting method, a new finite difference method is proposed to solve the velocity gradient equation on the S2m stream surface. In the finite difference scheme, the relative velocity derivative along the streamline direction is decomposed into two terms. One term uses forward difference, and the other uses backward difference. The difference schemes of all other parameter derivatives in the velocity gradient equation adopt forward difference. The method can guarantee the matrix main diagonal elements of the dominant, indicating stable convergence in solving the velocity field. Robustness analysis is performed for both methods, and the new finite difference method shows excellent superiority in stability. Finally, the finite difference method is applied to redesign the Krain impeller. Through computational fluid dynamics, the efficiency of the redesigned impeller at the design operating point is increased by approximately 0.3% and the pressure ratio by approximately 5%. These results show that the difference method is feasible to solve the S2m stream surface velocity gradient equation.

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Section: Introductionmentioning

confidence: 99%

A new finite difference method to solve the velocity gradient equation in streamline curvature method

Gong

Zhang

2016

Advances in Mechanical Engineering

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“…Most attention on the industrial large-scale compressors is paid to inverse design method and new optimization strategy (5)- (9) . Some of the related papers are associated with real gas thermodynamic properties.…”

Section: Literatures Reviewmentioning

confidence: 99%

Numerical Study on a High-Pressure Stage in Synthesis Gas Compressor

Liu

Wang

2012

JTST

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Numerical study on the first stage of the high-pressure casing in an industrial synthesis gas (syngas) compressor is presented here. Detailed flow field comparisons are made between impeller/stage models. The stage model is composed of impeller, vaneless diffuser, bend and return channel, while the impeller model is composed only with impeller and vaneless diffuser. Compared to the results from stage model, the impeller model results indicate that the predicted aerodynamic performance is higher, and operating range is wider in both stall and choke side. Under the same inlet volume flow rate, the blade pressure coefficients, Mach number and flow angle in the blade passage for both models are nearly the same, suggesting that the flow field data in the rotating impeller is to some degree credible for stage performance prediction. However, as the impeller model neglects the matching effect with the downstream stationary parts, there needs some correction for stage working range with stable operation. Besides, the internal flow fields of stage using air and syngas mediums are compared respectively. Results indicate that the aerodynamic performance and operation range are different for both mediums because of different density and gas constant. For the flow field of the whole stage, large discrepancy occurs in the leading edge of the return channel under the same inlet volume flow rate. It suggests that the existing air model stage couldn't be directly used for the syngas compressor and needs redesigning.

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“…The advanced CFD tools allow now the full optimization of centrifugal fan design, see Kim & Seo (2004); Schleer & Hong (2004); Zangeneh & Schleer (2004) works. For example, a three-dimensional unsteady viscous flow solution was numerically obtained by Khelladi et al (2005a) by means of powerful computational facilities and robust software, although with very consumptive calculation time.…”

Section: Aerodynamic Studymentioning

confidence: 99%