Unsteady flows in a single-stage transonic axial-flow fan stator row

Hathaway, Michael D.

doi:10.31274/rtd-180813-6889

Cited by 14 publications

(21 citation statements)

References 57 publications

(48 reference statements)

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“…To extend to a single stage, a blade row of stators (Stator 67) with 34 blades was placed downstream of the rotor row (Ref. 20). The axial distance from the trailing edge of the rotor to the leading edge of the stator is 85 percent of rotor axial chord at mid-span.…”

Section: Resultsmentioning

confidence: 99%

Aeroelastic Computations of a Compressor Stage Using the Harmonic Balance Method

Reddy¹,

Bakhle²

2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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Section: Resultsmentioning

confidence: 99%

Aeroelastic Computations of a Compressor Stage Using the Harmonic Balance Method

Reddy¹,

Bakhle²

2009

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

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“…To check the present method, we calculated the unsteady flows due to rotor/stator interaction in the first stage of NASA-67 compressor. The calculated results--unsteady velocity correlations u' v ' , 2 v' 2 --are compared with experimental data (Hathaway (1986)) at four axial positions: 0, 20, 50 and 100 percent of chord, see Fig.3, Fig. 4 and Fig.…”

Section: Resultsmentioning

confidence: 99%

Vortex Simulation of Rotor/Stator Interaction in Turbomachinery

Chen

1998

Volume 1: Turbomachinery

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A new numerical method is presented in this paper to simulate rotor/stator interaction in turbomachinery by use of a vortex method based on a Lagrangian frame. The algorithm takes the result from steady solution as input, which can give an initial description of the unsteady disturbance flow field. To calculate the unsteady response to these disturbances, the Lagrangian vortex method is used to capture the convective process, and the deterministic vortex scheme to approximate the viscous diffusion process. The application of Baldwin-Lomax turbulence model in wakes is developed, so as to overcome the difficulties such as the much higher calculated viscosity in the outer region than that in the boundary regions, and the difficulty in continuously tracing moving wake centerlines encounted by other numerical methods. The agreement between the computational and experimental results is generally good. The sweeping characteristic of wakes, the influence of unsteadiness on incidence and the decaying features of unsteady velocities, pressure are included in the paper.

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“…Although attempts were made to quantify the impact of these mechanisms (for example Kemp and Sears [1]) more than 40 years ago, measurement and computational methods have only recently advanced to an extent that allows a more definitive analysis. See Hathaway [2], Smith [3], and Van Zante [4] among others, for an overview of research on a wide range of unsteady phenomena.…”

Section: Introductionmentioning

confidence: 99%

“…The measurements hint at the possibility for interaction effects to be significant in some machines. Other data sets of note include that of Williams [6] in a close-coupled, multi-stage, high-speed compressor, Hathaway [2] in a looselycoupled transonic fan stage, Ottavy, et al [7] of IGV-transonic rotor interaction in an HP compressor stage, and Estevadeordal et al [8] for DPIV measurements of IGV-transonic rotor interaction.…”

Section: Introductionmentioning

confidence: 99%

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Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

Zante

Chen

2002

Volume 5: Turbo Expo 2002, Parts a and B

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Blade row interaction effects on loss generation in compressors have received increased attention as compressor work-per-stage and blade loading have increased. Two dimensional Laser Doppler Velocimeter measurements of the velocity field in a NASA transonic compressor stage show the magnitude of interactions in the velocity field at the peak efficiency and near stall operating conditions. The experimental data are presented along with an assessment of the velocity field interactions. In the present study the experimental data are used to confirm the fidelity of a three-dimensional, time-accurate, Navier Stokes calculation of the stage using the MSU-TURBO code at the peak efficiency and near stall operating conditions. The simulations are used to quantify the loss generation associated with interaction phenomena. At the design point the stator pressure field has minimal effect of the rotor performance. The rotor wakes do have an impact on loss production in the stator passage at both operating conditions. A method for determining the potential importance of blade row interactions on performance is presented.

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Unsteady flows in a single-stage transonic axial-flow fan stator row

Cited by 14 publications

References 57 publications

Aeroelastic Computations of a Compressor Stage Using the Harmonic Balance Method

Aeroelastic Computations of a Compressor Stage Using the Harmonic Balance Method

Vortex Simulation of Rotor/Stator Interaction in Turbomachinery

Blade Row Interaction Effects on the Performance of a Moderately Loaded NASA Transonic Compressor Stage

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