A study on the rotating stall in vaneless diffusers of centrifugal fans. 1st Report. Rotational speeds of stall cells, critical inlet flow angle.

Tsurusaki, Hiromu; Imaichi, Kensaku; Miyake, Ryo

doi:10.1299/kikaib.52.2930

Cited by 7 publications

(12 citation statements)

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“…Also in the last few decades many studies were carried out using both theoretical and experimental methods on instabilities downstream of the impeller. Theoretical analyses include Jansen [3,4], Senoo et al [5,6] [25], and Ji et al [26].…”

Section: The Current Design and Possible Effect Of Impeller Flow Exitmentioning

confidence: 99%

“…But the analysis carried out by Ljevar et al [10] showed strong influence of impeller on diffuser stability. Tsurusaki et al [25] studied rotational speeds of stall cells in vaneless diffusers and critical inlet flow angles for rotating stalls under the condition of no volute experimentally. They also correlated their experimental data and put forward a simple equation for the prediction of critical angle.…”

Section: The Current Design and Possible Effect Of Impeller Flow Exitmentioning

confidence: 99%

“…The casing region of such compressors consist of boundary layer developed at the shroud endwall and on the blades, and the superposition of a leading edge and passage shock wave system that can cause the boundary layers to strongly separate. Prior studies [e.g., 24,25,26] have found resistance of a boundary layer to separate in the presence of a given shock wave correlates with incompressible shape factor of the incoming boundary layer and its local total pressure. Walljets act to reduce shape factor and boost local total pressure in a manner that reduces potential for shock-induced separation.…”

Section: Nomentioning

confidence: 99%

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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: The Current Design and Possible Effect Of Impeller Flow Exitmentioning

confidence: 99%

Section: The Current Design and Possible Effect Of Impeller Flow Exitmentioning

confidence: 99%

Section: Nomentioning

confidence: 99%

See 1 more Smart Citation

Design and Testing of CO2 Compression Using Supersonic Shockware Technology

Williams¹,

Aarnio²,

Lupkes³

et al. 2010

View full text Add to dashboard Cite

show abstract

“…For two dimensional analysis, it was suggested the 2D core flow instability might be responsible for rotating stall. Generally, it is admitted that the effect of [11], Dazin et al [1,12], Dodds and Vahdati [13,14], Ferrara et al [15,16], Abdelhamid et al [17][18][19], Abidogun [20], Nishida and Kobayshi [21,22], Cellai et al [23], Tsurusaki et al [24], Suzuki et al [25], Caignaert et al [26]. The main research contents of these experimental studies were focused on several aspects: i.…”

Section: Introductionmentioning

confidence: 99%

Experimental Study and Theoretical Analysis of the Rotating Stall in a Vaneless Diffuser of Radial Flow Pump

Heng

Ouarzazi

2016

IOP Conf. Ser.: Earth Environ. Sci.

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This paper reports an experimental and theoretical study of rotating stall in a vaneless diffuser which is coupled with a radial impeller. The experiments were conducted at 22 flow rates for two rotating speed: 1200rpm and 1800rpm. The measurements have consisted of: i/ unsteady pressure measurements delivered by two microphones flush mounted on the vaneless diffuser, ii/ 9 steady pressure taps mounted in one radial line on the diffuser to measure the pressure recovery in the vaneless diffuser. The stability of each stall mode was also studied by a 2D linear analysis; and the theoretical prediction was compared to experimental observations. The capabilities and limits of such an approach to predict the development of rotating stall have been evaluated. A non-dimensional analysis of the pressure losses at outlet was conducted to evaluate the effect of the instability development on the performance of the diffuser. It has shown that the arising of rotating stall has a positive effect on the diffuser performance.

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“…The analysis of the experimental result of Tsurusaki, Imaichi and Miyake (1987) about the fields of the total and fluctuating velocities of rotating stall in the vaneless diffuser reveals furthermore that the longitudinal spiral vortex is centred on the through flow. The two vortices of the pair stay side by side in touch but without mixing because of their opposite rotational sense.…”

mentioning

confidence: 97%

Experimental Investigation of the Longitudinal-Vortex-Nature of Rotating Stall in Vaneless Diffusers of Centrifugal Compressors

Chen

Haupt

Seidel

et al. 1991

Volume 1: Turbomachinery

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Rotating stall in a vaneless diffuser of a centrifugal compressor has been found to be guided by Rossby waves, which are composed of branches of high and low pressures (Chen, Haupt and Rautenberg, 1990a). The branch of the high pressure leads the unstalled region and that of the low pressure leads the stalled region. The phase velocity of the Rossby waves is then the pattern speed of the stall cell.Finally, the origin of the vorticity of the longitudinal vortices along the through flow and the Rossby-wave front is derived based on the experimental results obtained by Hergt andJaberg (1988), andHide (1958).

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A study on the rotating stall in vaneless diffusers of centrifugal fans. 1st Report. Rotational speeds of stall cells, critical inlet flow angle.

Cited by 7 publications

References 0 publications

Design and Testing of CO2 Compression Using Supersonic Shockware Technology

Design and Testing of CO2 Compression Using Supersonic Shockware Technology

Experimental Study and Theoretical Analysis of the Rotating Stall in a Vaneless Diffuser of Radial Flow Pump

Experimental Investigation of the Longitudinal-Vortex-Nature of Rotating Stall in Vaneless Diffusers of Centrifugal Compressors

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