Swirling Impeller Flow

Krain, H.

doi:10.1115/1.3262157

Cited by 114 publications

(76 citation statements)

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“…In the pressure side passage, the profile is nearly linear across the pitch. The profile of the suction side passage is similar to the discharge profile reported by Krain (1987) for an impeller with 30 degrees of backsweep. The discharge profile of that impeller showed the through-flow velocity increasing toward the hub and less so toward the pressure surface with a slight depression near midpitch.…”

Section: Suction Side Passagesupporting

confidence: 68%

“…The velocity profiles at each spanwise location contain a small "+" at points where the velocity magnitudes are reported. The velocity distribution shown in Figure 6 increases toward the suction surface in a linear fashion and is similar to inducer velocity profiles that were reported by Eckardt (1976), Krain (1987), and Hathaway, et al (1993).…”

Section: Inlet Regionsupporting

confidence: 65%

“…The vortex first migrates toward the pressure surface and then toward the suction surface. Krain (1987) showed that the downstream regions of low momentum fluid have the characteristics of a vortex flow.…”

Section: Introductionmentioning

confidence: 99%

“…The first reported measurements were obtained by Eckardt (1976) using a Laser-2-Focus Velocimeter. Since then, several other researchers ( Adler and Levy, 1979;Eckardt, 1979;Krain, 1981Krain, , 1987Ahmed and Elder, 1990;Pak et al, 1993;Krain et al, 1995) have used laser anemometers to measure the flow fields within high-speed centrifugal impellers configured with both vaned and vaneless diffusers. Hathaway et al (1993) reported results from a study in a large low-speed compressor.…”

Section: Introductionmentioning

confidence: 99%

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Laser Anemometer Measurements of the Flow Field in a 4:1 Pressure Ratio Centrifugal Impeller

Skoch

Prahst²,

Wernet

et al. 1997

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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A laser-doppler anemometer was used to obtain flow-field velocity measurements in a 4:1 pressure ratio, 4.54 kg/s (10 lbm/s), centrifugal impeller, with splitter blades and backsweep, which was configured with a vaneless diffuser. Measured through-flow velocities are reported for ten quasi-orthogonal survey planes at locations ranging from 1% to 99% of main blade chord. Measured through-flow velocities are compared to those predicted by a 3-D viscous steady flow analysis (Dawes) code.The measurements show the development and progression through the impeller and vaneless diffuser of a through-flow velocity deficit which results from the tip clearance flow and accumulation of low momentum fluid centrifuged from the blade and hub surfaces. Flow traces from the CFD analysis show the origin of this deficit which begins to grow in the inlet region of the impeller where it is first detected near the suction surface side of the passage. It then moves toward the pressure side of the channel, due to the movement of tip clearance flow across the impeller passage, where it is cut by the splitter blade leading edge. As blade loading increases toward the rear of the channel the deficit region is driven back toward the suction surface by the cross-passage pressure gradient. There is no evidence of a large wake region that might result from flow separation and the impeller efficiency is relatively high. The flow field in this impeller is quite similar to that documented previously by NASA Lewis in a large low-speed backswept impeller.

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Section: Suction Side Passagesupporting

confidence: 68%

Section: Inlet Regionsupporting

confidence: 65%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Laser Anemometer Measurements of the Flow Field in a 4:1 Pressure Ratio Centrifugal Impeller

Skoch

Prahst²,

Wernet

et al. 1997

Volume 1: Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

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show abstract

“…Karin [4] also measured a centrifugal compressor with a pressure ratio of 4. Hah [5] performed a 3D numerical simulation of a centrifugal compressor.…”

Section: Introductionmentioning

confidence: 99%

Analysis and Improvement of a Two-Stage Centrifugal Compressor Used in an MW-Level Gas Turbine

Zhu

Ren

et al. 2018

Applied Sciences

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Featured Application: A two-stage centrifugal compressor used in an MW-level gas turbine is optimized, especially for diffusers. The experiences can also be used for other similar equipment. Abstract:The performance of a low/high-pressure-stage centrifugal compressor in a land-use MW-level gas turbine with a pressure ratio of approximately 11 is analyzed and optimized with a 1D aerodynamic design and modeling optimization system. 1D optimization results indicate that the diameter ratio of the low-pressure-stage centrifugal compressor with a vane-less diffuser, and the divergent angle of the high-pressure-stage centrifugal compressor with a vaned diffuser, are extremely large and result in low efficiency. Through modeling design and optimization system analysis, a tandem vaned diffuser is used in the low-pressure stage, and a tandem vaned diffuser with splitter vanes is adopted in the high-pressure stage. Computational fluid dynamics (CFD) results show that the pressure ratio and efficiency of the optimized low/high-pressure-stage centrifugal compressor are significantly improved. Coupling calculations of the low/high-pressure stage of the original and optimized designs are conducted based on the results of MW-level gas turbine cycles. CFD results show that the pressure ratio and efficiency of the optimized two-stage centrifugal compressor increase by approximately 8% and 4%, respectively, under three typical load conditions of 100%, 90%, and 60%.

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2010

Aerothermodynamics of Turbomachinery

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Swirling Impeller Flow

Cited by 114 publications

References 0 publications

Laser Anemometer Measurements of the Flow Field in a 4:1 Pressure Ratio Centrifugal Impeller

Laser Anemometer Measurements of the Flow Field in a 4:1 Pressure Ratio Centrifugal Impeller

Analysis and Improvement of a Two-Stage Centrifugal Compressor Used in an MW-Level Gas Turbine

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