Pressure and Temperature Distortion Testing of a Two-Stage Centrifugal Compressor

Cousins, William T.; Dalton, K. K.; Andersen, T. T.; Bobula, George A.

doi:10.1115/93-gt-118

Cited by 3 publications

(1 citation statement)

References 1 publication

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“…Flow nonuniformity at the impeller inlet, which is generally known as ''inlet distortion'', has been investigated with experiments and numerical simulations to analyze the effects of inlet distortions on centrifugal compressors. [2][3][4][5][6][7] The investigations indicated that inlet distortions mainly influenced the performances of centrifugal compressors by introducing nonuniform pressure and flow angle distributions to the impeller inlet, which could cause incidences, boundary layer separations and possibly rotating stall of impellers.…”

Section: Introductionmentioning

confidence: 99%

Flow measurement and simulation of a radial inlet for centrifugal compressor

Han

Mao

Tan³

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part A:

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This paper presents an experimental and numerical research on the internal flow of a typical radial inlet for centrifugal compressor. Detailed flow measurements were carried out with five-hole probes, consisting of 106 sampling holes and 2178 measuring points. Automatic calibrating and measuring systems, which made the probe calibrations, measurements and data acquisitions controlled by computer, were developed and used to accelerate the flow measurements. Since separations and vortices in the radial inlet were not able to be accurately measured by five-hole probes, numerical simulation was adopted to assist in the flow analysis of the radial inlet in the present study. The investigation indicated that there were five main flow separations and vortices in the present radial inlet. Four of them were generated in the plenum, making the plenum the primary cause of the flow loss and the major factor of the flow distortions in the radial inlet. The last flow separation was generated on the inlet side of the flange at the 90° turning and extended to the exit of the axial duct. Besides, the symmetrical tangential flows in the radial inlet made positive and negative yaw angles with absolute value up to over 15° distributed in the tangential direction of the radial inlet’s exit, which will probably increase the incidence loss in the blade passages and negatively affect the work capability of the impeller. Based on the flow analysis and discussions, preliminary suggestions are proposed to provide references for the improvements of radial inlet.

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Section: Introductionmentioning

confidence: 99%

Flow measurement and simulation of a radial inlet for centrifugal compressor

Han

Mao

Tan³

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part A:

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History, Philosophy, Physics, and Future Directions of Aircraft Propulsion System/Inlet Integration

Cousins

2004

Volume 2: Turbo Expo 2004

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This work provides a historical perspective of the developments of propulsion system inlet/engine integration. The flow physics of inlet distortion are discussed, along with the stability effects on the engine compression systems. Throughout the document, both commercial and military applications are considered. Developments in analyses from the original works characterizing inlet distortion, the use of distortion descriptors and early modeling concepts, and the modeling and simulation required today are reviewed. The special requirements and testing techniques necessary to adequately describe inlet distortion and the effects on the propulsion system are summarized. The aspects of pressure distortion, temperature distortion, and swirl are addressed and the physics of interaction described. The compression system response to different types of distortion is discussed with the interaction with various compression system components and designs explained. Axial and centrifugal compressors are covered, as the resulting physics of the inlet distortion effects on each has a different characteristic. An overview of the necessary flow physics to consider in the integration of compression systems in both low and high-Mach number applications is presented.

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Numerical Investigation on the Performance of a Transonic Axial Compressor with Inlet Distortion and Low Reynolds Number

Zhu

Yan

et al. 2022

Energies

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The performance and stability of the transonic fan stage with a nonuniform inflow is a key issue in aero engine operation, and the coupling of inlet distortion and low Reynolds numbers at high altitude creates more severe challenges to aero engines. This work used computational methods to explore the performance and stability of a transonic fan stage with inlet distortion and a low Reynolds number. To investigate this issue, the transonic fan stage NASA stage 67 with a 180° total pressure distortion at a low Reynolds number was selected as the test case. Full-annulus 3D unsteady simulations were conducted to reveal the details of the flow field under coupling conditions. The computational results under different conditions were analyzed and showed that the coupling effect was not linearly stacked with single factors. The low Reynolds number in the coupling case thickened the boundary layer on the blade surface, and, on the one hand, the profile loss in the hub region increased. On the other hand, the structure of shock wave was converted in the tip region, which increased the shock loss significantly. In addition, the variation in the shock wave structure reconstructed the pressure distribution on the blade surface, allowing the fluid to migrate to the tip region, which affected the tip flow structure and ultimately delayed the stability boundary.

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Pressure and Temperature Distortion Testing of a Two-Stage Centrifugal Compressor

Cited by 3 publications

References 1 publication

Flow measurement and simulation of a radial inlet for centrifugal compressor

Flow measurement and simulation of a radial inlet for centrifugal compressor

History, Philosophy, Physics, and Future Directions of Aircraft Propulsion System/Inlet Integration

Numerical Investigation on the Performance of a Transonic Axial Compressor with Inlet Distortion and Low Reynolds Number

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