Development and application of a CFD solver to the simulation of centrifugal compressors

Niazi, Saeid; Stein, A.; Sankar, Lakshmi N.

doi:10.2514/6.1998-934

Cited by 11 publications

(5 citation statements)

References 9 publications

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“…Preliminary code validation studies for a NASA Lewis Research Center low-speed centrifugal compressor (LSCC) con guration were reported in Ref. 19. In Ref.…”

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confidence: 99%

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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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“…Preliminary code validation studies for a NASA Lewis Research Center low-speed centrifugal compressor (LSCC) con guration were reported in Ref. 19. In Ref.…”

mentioning

confidence: 99%

“…In Ref. 19, this CFD code was also used to study the effect of steady bleeding on the performance of the compressor. It was shown that bleed valves placed in the diffuser walls help to improve the ow pattern within the diffuser, and eliminate diffuser stall.…”

mentioning

confidence: 99%

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Stein

Niazi

Sankar

2000

Journal of Propulsion and Power

Self Cite

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“…Also, with the availability of reliable experimental test data by AGARD 21 , researchers now have access to a plethora of data for validation of turbomachinery codes. Since then a number of three dimensional CFD codes capable of analyzing single and multiple blade passage turbomachinery flow have been developed by many researchers [22][23][24][25][26][27][28][29] .…”

Section: Computational Studies On Compressor Performancementioning

confidence: 99%

A First-Principles Based Methodology for Design of Axial Compressor Configurations

Iyengar

Sankar

Denney

2007

Volume 6: Turbo Expo 2007, Parts a and B

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A multi-objective technique for designing single stage compressors is described. The blade geometry is defined as a function of known parametric equations, and the coefficient multipliers are viewed as design variables. A design of experiment approach is used to reduce the large combinations of design variables into a smaller subset. A response surface method is used to approximate the performance (total pressure rise, and adiabatic efficiency) as a function of design variables, and an optimum configuration is determined. This method has been applied to a rotor-stator combination similar to NASA Stage 35 with encouraging results.

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“…Apart from conducting experiments, another efficient way to investigate the complex flow field in a centrifugal compressor is computational fluid dynamics Turbomachinery Laboratory, State Key Laboratory of Automotive Safety and Energy, Tsinghua University, Beijing, People's Republic of China (CFD). Hah and Wennerstrom 6 and Niazi et al 7 developed CFD codes to investigate the flow field inside a centrifugal compressor. It is known that in centrifugal compressors the hydraulic diameter of the flow passage is small compared with the passage length; therefore, the secondary flow is dominant because of the centrifugal force and the Coriolis force.…”

Section: Introductionmentioning

confidence: 99%

Improvement in the stability of a turbocharger centrifugal compressor by tip leakage control

Mirzaee

Zheng

Lin

2016

Proceedings of the Institution of Mechanical Engineers, Part D:

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The occurrence of surge or stall in a centrifugal compressor and the role of the tip clearance flow in the instability in the centrifugal compressor are investigated in this study. A computational method is used to study the flow field in the centrifugal compressor in order to gain a better understanding of the surge or stall mechanism. It is found that, near surge or stall conditions, the tip leakage flow at the leading edge deflects more upstream; as the deflection increases, a more severe spillage occurs which finally leads to instability of the compressor. A ring air jet injection is used to eliminate the instabilities and to extend the stable flow range of the compressor. Using an air jet injection, the stable flow range of the compressor was successfully increased with minimal decrease in the efficiency of the compressor. The effects of different injection parameters such as the mass flow, the yaw angle, the injection angle, the slot width and the slot distance on the compressor flow field are studied, and an optimum design for the air jet injection is developed. Further investigation of the compressor with the optimum injection configuration shows that, near surge or stall conditions, the tip leakage at the leading edge is still under control, manifesting a much smaller spillage than does the Dresser–Rand Datum compressor without an air injection. The dominant factor for the instability of the compressor with an injection is found to be the leading-edge separation rather than the tip leakage.

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Development and application of a CFD solver to the simulation of centrifugal compressors

Cited by 11 publications

References 9 publications

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

Computational Analysis of Stall and Separation Control in Centrifugal Compressors

A First-Principles Based Methodology for Design of Axial Compressor Configurations

Improvement in the stability of a turbocharger centrifugal compressor by tip leakage control

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