NASA low-speed centrifugal compressor for fundamental research

Wood, J. R.; Adam, Pad W.; Buggele, A. E.

doi:10.2514/6.1983-1351

Cited by 17 publications

(14 citation statements)

References 7 publications

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“…1. This impeller has extensively been tested by Hathaway et al 25 and Wood et al 26 at the NASA Lewis Research Center, providing a well-documented case for CFD code validation purposes. The compressor characteristics are given next: Impeller: 20 full blades with 55-deg backsweep; inlet diameter: 0.87 m; exit diameter: 1.52 m; tip clearance: 2.54 mm (1.8% of blade height at trailing edge); and design conditions: mass ow rate = 30 kg/s, rotational speed = 1862 rpm, total pressure ratio = 1.14, and adiabatic ef ciency = 0.922.…”

Section: Resultsmentioning

confidence: 98%

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Stein

Niazi

Sankar

2000

Journal of Propulsion and Power

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A three-dimensional compressible Navier-Stokes code has been used to model the steady and unsteady ow eld within a low-speed centrifugal compressor con guration tested at NASA Lewis Research Center. Near-design conditions, the performance map, pressure eld, and the velocity eld were in good agreement with measured data. At off-design conditions, the calculations show that ow reversal rst occurs near the blade leading edge. If left unchecked, the reversed-ow region grows spatially and temporally. Injection of air upstream of the compressor face was found to modify the local ow near the blade leading edge and to suppress rotating stall and surge. Even a moderate amount of air, typically around 5% of the total mass ow rate, was suf cient to extend the useful operating range of the compressor. Nomenclature A= area F = inviscid ux vector Çm = mass ow rate n = unit normal vector P 0 = stagnation pressure p = static pressure q = state vector R = viscous ux vector R Inlet = leading-edge tip radius S = surface t = time t ¤ = time at instance of part-span stall U t = leading-edge tip velocity V = velocity vector V G = vector of grid velocities a , b = injection angles q = density Subscripts in = in ow property n = normal property out = out ow property 1 = far-eld property

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Section: Resultsmentioning

confidence: 98%

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Stein

Niazi

Sankar

2000

Journal of Propulsion and Power

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“…The NASA Low-Speed Centrifugal Compressor (LSCC) is an experimental facility designed to duplicate the essential flow physics of high-speed subsonic centrifugal compressor flow fields in a large low-speed machine in which very detailed investigations of the flow field can be made. A complete description of the facility is provided by Wood, et al, (1983) and Hathaway, et al, (1991).…”

Section: Test Compressormentioning

confidence: 99%

“…The LSCC was designed to generate a flow field which is aerodynamically similar to that found in high-speed subsonic centrifugal compressors, as described by Wood, et al, (1983) and Hathaway, et a!., (1991). If the flow field which has been investigated in the LSCC can be shown to indeed be similar to that found in actual subsonic centrifugal compressors, then the results presented here can be used to assess the accuracy of Navier-Stokes analyses and the lessons learned can be used with confidence when analyzing actual high-speed impellers.…”

Section: Fidelity Of the Low Speed Compressor Flow Field Simulationmentioning

confidence: 99%

Experimental and Computational Investigation of the NASA Low-Speed Centrifugal Compressor Flow Field

Hathaway

Chriss

Wood

et al. 1992

Volume 1: Turbomachinery

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An experimental and computational investigation of the NASA Low-Speed Centrifugal Compressor (LSCC) flow field has been conducted using laser anemometry and Dawes' 3D viscous code. The experimental configuration consists of a backswept impeller followed by a vaneless diffuser. Measurements of the three-dimensional velocity field were acquired at several measurement planes through the compressor. The measurements describe both the throughflow and secondary velocity field along each measurement plane. In several cases the measurements provide details of the flow within the blade boundary layers. Insight into the complex flow physics within centrifugal compressors is provided by the computational analysis, and assessment of the CFD predictions is provided by comparison with the measurements. Five-hole probe and hot-wire surveys at the inlet and exit to the rotor as well as surface flow visualization along the impeller blade surfaces provide independent confirmation of the laser measurement technique. NOMENCLATUREUnit vector in the measured velocity component direction J Streamwise measurement grid indice Local streamwise grid direction vector ,,, Unit vector in local meridional grid direction gy Unit vector in local pitchwise grid direction gs Unit vector in local spanwise grid direction m/m 9 Non-dimensional shroud meridional distance N,pp Number of encoder counts per blade pitch Np Number of impeller blade passages PS Pressure surface r/r t Radius non-dimensionalized by exit tip radius SS Suction surface Ut Impeller tip speed, m/sec V Absolute total velocity vector, m/sec V, Mean velocity component measured in direction c, m/sec V. Meridional velocity component, m/sec Vp Pitchwise secondary velocity component, m/sec VQ"r Quasi-meridional velocity component, m/sec Vr Radial velocity component, m/sec V, Spanwise secondary velocity component, positive towards the shroud, m/sec Vst Velocity component tangent to the shroud meridional direction, m/sec VT Total relative velocity, m/sec Vx Axial velocity component, m/sec V0 Relative tangential velocity component, m/sec a Flow pitch angle, deg., a = tan -t (Vr /V= ) /^ Absolute flow angle, deg., 3 = tan -t (V9/Vqm ) 0 Tangential coordinate, radians Superscripts -Passage average

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“…The new low-speed centrifugal compressor facility at NASA Lewis Research Center (Wood et al, 1983) has been built to enable a more thorough understanding of subsonic flow in the complex geometric channels of centrifugal compressors to be obtained. NASA is planning an experimental program to obtain "benchmark" experimental data to verify three-dimensional viscous flow codes and to provide data with which to develop more sophisticated models of the various physical phenomena occuring in a centrifugal compressor.…”

Section: Introduction Nasa Low-speed Centrifugal Compressor Research mentioning

confidence: 99%

A Prediction of 3-D Viscous Flow and Performance of the NASA Low-Speed Centrifugal Compressor

Moore¹,

Moore²

1990

Volume 1: Turbomachinery

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A p r e d i c t i o n of t h e three-dimensional t u r b u l e n t flow i n t h e NASALow-Speed C e n t r i f u g a l Compressor I m p e l l e r has been made. The c a l c u l at i o n was made f o r t h e compressor design c o n d i t i o n s with t h e s p e c i f i e duniform t i p c l e a r a n c e gap. The predicted performance is s i g n i f i c a n t l y worse than t h a t p r e d i c t e d i n t h e NASA design study. This i s explained by t h e high t i p leakage flow i n t h e p r e s e n t c a l c u l a t i o n and by t h e d i f f e r e n t model adopted f o r t i p leakage flow mixing. The c a l c u l a t i o n g i v e s an accumulation of high l o s s e s i n t h e shroud/pressure-side quadr a n t near t h e e x i t of t h e i m p e l l e r . It a l s o p r e d i c t s a region of meridi o n a l backflow near t h e shroud w a l l . Both of t h e s e flow f e a t u r e s should be e x t e n s i v e enough i n t h e NASA i m p e l l e r t o a l

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NASA low-speed centrifugal compressor for fundamental research

Cited by 17 publications

References 7 publications

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Experimental and Computational Investigation of the NASA Low-Speed Centrifugal Compressor Flow Field

A Prediction of 3-D Viscous Flow and Performance of the NASA Low-Speed Centrifugal Compressor

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