The Influence of Shroud Curvature and Other Related Factors on Impeller Performance Characteristics

Sorokes, James M.; Kopko, Jason A.; Geise, Paul R.; Hinklein, Angelina L.

doi:10.1115/gt2009-60109

Cited by 4 publications

(1 citation statement)

References 2 publications

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“…Sorokes et al [29] carried out an extensive work to determine the impact of shroud curvature on the performance of a centrifugal impeller or stage. They showed that the value of L ax /d 2 and related curvature geometry are especially important in the design of high inlet relative Mach number centrifugal compressor impellers.…”

Section: Effect Of Impeller Axial Length L Ax On Impeller Flowmentioning

confidence: 99%

Design and Testing of CO2 Compression Using Supersonic Shockware Technology

Williams¹,

Aarnio²,

Lupkes³

et al. 2010

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Documentation of work performed by Ramgen and subcontractors in pursuit of design and construction of a 10 MW supersonic CO 2 compressor and supporting facility. The compressor will demonstrate application of Ramgen's supersonic compression technology at an industrial scale using CO 2 in a closed-loop.The report includes details of early feasibility studies, CFD validation and comparison to experimental data, static test experimental results, compressor and facility design and analyses, and development of aero tools. Executive SummaryRamgen is designing, building and testing a novel CO 2 compressor demonstrator capable of providing 10:1 single-stage pressure ratio for CO 2 sequestration applications. The project will demonstrate that Ramgen's supersonic compression technology is more efficient and less expensive than other compression options available in the foreseeable future.This report documents work performed by Ramgen and subcontractors in pursuit of design and construction of a 10 MW supersonic CO 2 compressor and supporting facility. The compressor will demonstrate application of Ramgen's supersonic compression technology at an industrial scale using CO 2 in a closed-loop environment.A comprehensive Configuration/Feasibility Study was conducted, concluding with a Large Machine Feasibility Review. The review addressed mechanical issues including rotor and static structure, rotordynamics, seals and bearings, drivetrain, controls and instrumentation, maintenance and access, and compressor layout. Aero focus included all static and rotating aerodynamics, supersonic starting, efficient CFD workflow and system performance. After closing out action items from this review, the demonstration unit design was declared feasible and authorization was given for Engineering to proceed into Preliminary Design with the selected rotor configuration.Extensive numerical predictions of complex 3D shock wave / boundary layer interactions were performed to test ability of the numerical algorithms employed to capture complex 3D turbulent boundary layer separation phenomena observed in experiments. These simulations were performed for linear or static configurations, rather than rotating, due to the availability of linear test data. Static and rotating tests were undertaken at the Naval Postgraduate School to investigate the effects of boundary layer control methods on shock-boundary layer interaction.While not yet complete, the results so far indicate very good CFD correlation with experimental data in the critical interaction regions.Ramgen contracted with Michigan State University's Turbomachinery Laboratory to experimentally investigate vaned diffuser designs under high Mach number and high flow angle operating conditions. MSU's existing test rig made them a strong candidate for this test. The program's first phase was to evaluate and confirm feasibility of achieving relevant Mach and flow angles with a new rotor design. Unfortunately, the feasibility study was unable to identify a test rotor design capable of produ...

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Section: Effect Of Impeller Axial Length L Ax On Impeller Flowmentioning

confidence: 99%

Design and Testing of CO2 Compression Using Supersonic Shockware Technology

Williams¹,

Aarnio²,

Lupkes³

et al. 2010

View full text Add to dashboard Cite

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Stationary Component Optimization and the Resultant Improvement in the Performance Characteristics of a Radial Compressor Stage

Fakhri¹,

Sorokes²,

Vézier³

et al. 2013

Volume 6C: Turbomachinery

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This paper is a follow-up to work published by Sorokes et al. [16] regarding a diffuser flow-field phenomenon, identified as a precursor to stall in a centrifugal stage. The earlier work provided greater detail on the phenomenon that occurred, including further details on the CFD analyses done to investigate the phenomenon and the trends observed in the test data. The numerical and experimental results described in the earlier work were used as a foundation in developing improved stationary components of another stage of similar design whose surge margin fell short of expectation, with the goal of improving its surge margin and overall performance. The study focused specifically on improving the flow characteristics in the diffuser and return channel by optimizing the geometry. The improvement in surge margin and overall performance was first verified numerically (through CFD analysis) and then experimentally via scale model testing. The paper will provide an overview of the centrifugal stage that was tested along with a description of the test vehicle, operating conditions and instrumentation used. The paper will also include a description of the numerical work completed; i.e., the CFD code used, computational domain considered and boundary conditions applied. Comparisons of the trends observed in the experimental and numerical work will be offered and the agreement between the numerical and empirical results will be assessed. Finally, performance comparisons of the optimized stage with the previous stage will also be presented.

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