Viscous throughflow modeling of axial compressor bladerows using a tangential blade force hypothesis

Gallimore, S J

doi:10.1115/1.2841775

Title: Viscous throughflow modeling of axial compressor bladerows using a tangential blade force hypothesis

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Abstract

This paper describes the modeling of axial compressor blade rows in an axisymmetric viscous throughflow method. The basic method, which has been reported previously, includes the effects of spanwise mixing, using a turbulent diffusion model, and endwall shear within the throughflow calculation. The blades are modeled using a combination of existing two-dimensional blade performance predictions for loss and deviation away from the annulus walls and a novel approach using tangential blade forces in the endwall regions. Relatively simple assumptions about the behavior of the tangential static pressure force imposed by the blades allow the secondary deviations produced by tip clearance flows and the boundary layer flows at fixed blade ends to be calculated in the axisymmetric model. Additional losses are assigned in these regions based on the calculated deviations. The resulting method gives realistic radial distributions of loss and deviation across the whole span at both design and off-design operating conditions, providing a quick method of estimating the magnitudes of these effects in the preliminary design process. Results from the method are compared to measured data in low and high-speed compressors and multistage three-dimensional viscous CFD predictions.

Authors:

Gallimore, S J ^[1]

Rolls-Royce PLC, Derby (United Kingdom)

Publication Date:: Thu Oct 01 00:00:00 EDT 1998

Sponsoring Org.:: USDOE

OSTI Identifier:: 316081

Report Number(s):: CONF-970604-
Journal ID: JOTUEI; ISSN 0889-504X; TRN: IM9908%%161

Resource Type:: Journal Article

Journal Name:: Journal of Turbomachinery

Additional Journal Information:: Journal Volume: 120; Journal Issue: 4; Conference: 42. international gas turbine and aeroengine congress and exhibition, Orlando, FL (United States), 2-5 Jun 1997; Other Information: PBD: Oct 1998

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS; GAS COMPRESSORS; COMPRESSOR BLADES; GAS FLOW; MATHEMATICAL MODELS; VISCOUS FLOW

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                    Gallimore, S J. Viscous throughflow modeling of axial compressor bladerows using a tangential blade force hypothesis.  United States: N. p., 1998. 
        Web.  doi:10.1115/1.2841775.

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                    Gallimore, S J. Viscous throughflow modeling of axial compressor bladerows using a tangential blade force hypothesis.  United States.  https://doi.org/10.1115/1.2841775

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                    Gallimore, S J. 1998.  
        "Viscous throughflow modeling of axial compressor bladerows using a tangential blade force hypothesis".  United States.  https://doi.org/10.1115/1.2841775.

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@article{osti_316081,

  title        = {Viscous throughflow modeling of axial compressor bladerows using a tangential blade force hypothesis},

  author       = {Gallimore, S J},

  abstractNote = {This paper describes the modeling of axial compressor blade rows in an axisymmetric viscous throughflow method. The basic method, which has been reported previously, includes the effects of spanwise mixing, using a turbulent diffusion model, and endwall shear within the throughflow calculation. The blades are modeled using a combination of existing two-dimensional blade performance predictions for loss and deviation away from the annulus walls and a novel approach using tangential blade forces in the endwall regions. Relatively simple assumptions about the behavior of the tangential static pressure force imposed by the blades allow the secondary deviations produced by tip clearance flows and the boundary layer flows at fixed blade ends to be calculated in the axisymmetric model. Additional losses are assigned in these regions based on the calculated deviations. The resulting method gives realistic radial distributions of loss and deviation across the whole span at both design and off-design operating conditions, providing a quick method of estimating the magnitudes of these effects in the preliminary design process. Results from the method are compared to measured data in low and high-speed compressors and multistage three-dimensional viscous CFD predictions.},

  doi          = {10.1115/1.2841775},

  url          = {https://www.osti.gov/biblio/316081},
  journal      = {Journal of Turbomachinery},
number       = 4,

  volume       = 120,

  place        = {United States},

  year         = {Thu Oct 01 00:00:00 EDT 1998},

  month        = {Thu Oct 01 00:00:00 EDT 1998}

}

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