The effect of inlet boundary layer thickness on the flow within an annular S-shaped duct

Sonoda, T; Arima, T; Oana, M

doi:10.1115/1.2841361

Title: The effect of inlet boundary layer thickness on the flow within an annular S-shaped duct

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Abstract

Experimental and numerical investigations were carried out to gain a better understanding of the flow characteristics within an annular S-shaped duct, including the effect of the inlet boundary layer (IBL) on the flow. A duct with six struts and the geometry as that used to connect compressor spools on the experimental small two-spool turbofan engine was investigated. A curved downstream annular passage with similar meridional flow path geometry to that of the centrifugal compressor has been fitted at the exit of S-shaped duct. Two types of the IBL (i.e., thin and thick IBL) were used. Results showed that large differences of flow patterns were observed at the S-shaped duct exit between two types of IBL, though the value of net total pressure loss has not been remarkably changed. According to overall total pressure loss, which includes the IBL loss, the total pressure loss was greatly increased near the hub as compared to that for a thin one. For the thick IBL, a vortex pair related to the hub-side horseshoe vortex and the separated flow found at the strut trailing edge has been clearly captured in the form of the total pressure loss contours and secondary flow vectors, experimentally and numerically.more »« less

Authors:

Sonoda, T; Arima, T; Oana, M ^[1]

Honda R and D Co., Saitama (Japan). Wako Research Center

Publication Date:: Thu Jul 01 00:00:00 EDT 1999

Sponsoring Org.:: USDOE

OSTI Identifier:: 679306

Report Number(s):: CONF-980615-
Journal ID: JOTUEI; ISSN 0889-504X; TRN: IM9940%%126

Resource Type:: Journal Article

Journal Name:: Journal of Turbomachinery

Additional Journal Information:: Journal Volume: 121; Journal Issue: 3; Conference: American Society of Mechanical Engineers (ASME) turbo expo `98 - land, sea, air, Stockholm (Sweden), 2-5 Jun 1998; Other Information: PBD: Jul 1999

Country of Publication:: United States

Language:: English

Subject:: 33 ADVANCED PROPULSION SYSTEMS; GAS COMPRESSORS; GAS FLOW; ANNULAR SPACE; TURBOFAN ENGINES; PERFORMANCE; PRESSURE DROP

Citation Formats


                    Sonoda, T, Arima, T, and Oana, M. The effect of inlet boundary layer thickness on the flow within an annular S-shaped duct.  United States: N. p., 1999. 
        Web.  doi:10.1115/1.2841361.

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                    Sonoda, T, Arima, T, & Oana, M. The effect of inlet boundary layer thickness on the flow within an annular S-shaped duct.  United States.  https://doi.org/10.1115/1.2841361

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                    Sonoda, T, Arima, T, and Oana, M. 1999.  
        "The effect of inlet boundary layer thickness on the flow within an annular S-shaped duct".  United States.  https://doi.org/10.1115/1.2841361.

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@article{osti_679306,

  title        = {The effect of inlet boundary layer thickness on the flow within an annular S-shaped duct},

  author       = {Sonoda, T and Arima, T and Oana, M},

  abstractNote = {Experimental and numerical investigations were carried out to gain a better understanding of the flow characteristics within an annular S-shaped duct, including the effect of the inlet boundary layer (IBL) on the flow. A duct with six struts and the geometry as that used to connect compressor spools on the experimental small two-spool turbofan engine was investigated. A curved downstream annular passage with similar meridional flow path geometry to that of the centrifugal compressor has been fitted at the exit of S-shaped duct. Two types of the IBL (i.e., thin and thick IBL) were used. Results showed that large differences of flow patterns were observed at the S-shaped duct exit between two types of IBL, though the value of net total pressure loss has not been remarkably changed. According to overall total pressure loss, which includes the IBL loss, the total pressure loss was greatly increased near the hub as compared to that for a thin one. For the thick IBL, a vortex pair related to the hub-side horseshoe vortex and the separated flow found at the strut trailing edge has been clearly captured in the form of the total pressure loss contours and secondary flow vectors, experimentally and numerically. The high-pressure loss regions on either side of the strut wake near the hub may act on a downstream compressor performance. There is a much-distorted three-dimensional flow patterns at the exit of S-shaped duct. This means that the aerodynamic sensitivity of S-shaped duct to the IBL thickness is very high. Therefore, sufficient care is needed to design not only downstream aerodynamic components (for example, centrifugal impeller) but also upstream aerodynamic components (LPC OGV).},

  doi          = {10.1115/1.2841361},

  url          = {https://www.osti.gov/biblio/679306},
  journal      = {Journal of Turbomachinery},
number       = 3,

  volume       = 121,

  place        = {United States},

  year         = {Thu Jul 01 00:00:00 EDT 1999},

  month        = {Thu Jul 01 00:00:00 EDT 1999}

}

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