Simulation of multi-stage compressor at off-design conditions

Feng Wang, Mauro Carnevale, Luca Di Mare, Simon Gallimore

Research output: Chapter in Book/Report/Conference proceedingConference contribution

3 Citations (Scopus)

Abstract

Computational Fluid Dynamics (CFD) has been widely used for compressor design, yet the prediction of performance and stage matching for multi-stage, high-speed machines remain challenging. This paper presents the authors' effort to improve the reliability of CFD in multistage compressor simulations. The endwall features (e.g. blade fillet and shape of the platform edge) are meshed with minimal approximations. Turbulence models with linear and non-linear eddy viscosity models are assessed. The non-linear eddy viscosity model predicts a higher production of turbulent kinetic energy in the passages, especially close to the endwall region. This results in a more accurate prediction of the choked mass flow and the shape of total pressure profiles close to the hub. The non-linear viscosity model generally shows an improvement on its linear counterparts based on the comparisons with the rig data. For geometrical details, truncated fillet leads to thicker boundary layer on the fillet and reduced mass flow and efficiency. Shroud cavities are found to be essential to predict the right blockage and the flow details close to the hub. At the part speed the computations without the shroud cavities fail to predict the major flow features in the passage and this leads to inaccurate predictions of massflow and shapes of the compressor characteristic. The paper demonstrates that an accurate representation of the endwall geometry and an effective turbulence model, together with a good quality and sufficiently refined grid result in a credible prediction of compressor matching and performance with steady state mixing planes.

Original languageEnglish
Title of host publicationTurbomachinery
PublisherAmerican Society of Mechanical Engineers (ASME)
Volume2A-2017
ISBN (Electronic)9780791850787
DOIs
Publication statusPublished - 1 Jan 2018
EventASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017 - Charlotte, USA United States
Duration: 26 Jun 201730 Jun 2017

Conference

ConferenceASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017
CountryUSA United States
CityCharlotte
Period26/06/1730/06/17

ASJC Scopus subject areas

  • Engineering(all)

Cite this

Wang, F., Carnevale, M., Di Mare, L., & Gallimore, S. (2018). Simulation of multi-stage compressor at off-design conditions. In Turbomachinery (Vol. 2A-2017). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/GT201764964

Simulation of multi-stage compressor at off-design conditions. / Wang, Feng; Carnevale, Mauro; Di Mare, Luca; Gallimore, Simon.

Turbomachinery. Vol. 2A-2017 American Society of Mechanical Engineers (ASME), 2018.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Wang, F, Carnevale, M, Di Mare, L & Gallimore, S 2018, Simulation of multi-stage compressor at off-design conditions. in Turbomachinery. vol. 2A-2017, American Society of Mechanical Engineers (ASME), ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition, GT 2017, Charlotte, USA United States, 26/06/17. https://doi.org/10.1115/GT201764964
Wang F, Carnevale M, Di Mare L, Gallimore S. Simulation of multi-stage compressor at off-design conditions. In Turbomachinery. Vol. 2A-2017. American Society of Mechanical Engineers (ASME). 2018 https://doi.org/10.1115/GT201764964
Wang, Feng ; Carnevale, Mauro ; Di Mare, Luca ; Gallimore, Simon. / Simulation of multi-stage compressor at off-design conditions. Turbomachinery. Vol. 2A-2017 American Society of Mechanical Engineers (ASME), 2018.
@inproceedings{d9fb54b5e83a46b9a9c55fff2f612132,
title = "Simulation of multi-stage compressor at off-design conditions",
abstract = "Computational Fluid Dynamics (CFD) has been widely used for compressor design, yet the prediction of performance and stage matching for multi-stage, high-speed machines remain challenging. This paper presents the authors' effort to improve the reliability of CFD in multistage compressor simulations. The endwall features (e.g. blade fillet and shape of the platform edge) are meshed with minimal approximations. Turbulence models with linear and non-linear eddy viscosity models are assessed. The non-linear eddy viscosity model predicts a higher production of turbulent kinetic energy in the passages, especially close to the endwall region. This results in a more accurate prediction of the choked mass flow and the shape of total pressure profiles close to the hub. The non-linear viscosity model generally shows an improvement on its linear counterparts based on the comparisons with the rig data. For geometrical details, truncated fillet leads to thicker boundary layer on the fillet and reduced mass flow and efficiency. Shroud cavities are found to be essential to predict the right blockage and the flow details close to the hub. At the part speed the computations without the shroud cavities fail to predict the major flow features in the passage and this leads to inaccurate predictions of massflow and shapes of the compressor characteristic. The paper demonstrates that an accurate representation of the endwall geometry and an effective turbulence model, together with a good quality and sufficiently refined grid result in a credible prediction of compressor matching and performance with steady state mixing planes.",
author = "Feng Wang and Mauro Carnevale and {Di Mare}, Luca and Simon Gallimore",
year = "2018",
month = "1",
day = "1",
doi = "10.1115/GT201764964",
language = "English",
volume = "2A-2017",
booktitle = "Turbomachinery",
publisher = "American Society of Mechanical Engineers (ASME)",
address = "USA United States",

}

TY - GEN

T1 - Simulation of multi-stage compressor at off-design conditions

AU - Wang, Feng

AU - Carnevale, Mauro

AU - Di Mare, Luca

AU - Gallimore, Simon

PY - 2018/1/1

Y1 - 2018/1/1

N2 - Computational Fluid Dynamics (CFD) has been widely used for compressor design, yet the prediction of performance and stage matching for multi-stage, high-speed machines remain challenging. This paper presents the authors' effort to improve the reliability of CFD in multistage compressor simulations. The endwall features (e.g. blade fillet and shape of the platform edge) are meshed with minimal approximations. Turbulence models with linear and non-linear eddy viscosity models are assessed. The non-linear eddy viscosity model predicts a higher production of turbulent kinetic energy in the passages, especially close to the endwall region. This results in a more accurate prediction of the choked mass flow and the shape of total pressure profiles close to the hub. The non-linear viscosity model generally shows an improvement on its linear counterparts based on the comparisons with the rig data. For geometrical details, truncated fillet leads to thicker boundary layer on the fillet and reduced mass flow and efficiency. Shroud cavities are found to be essential to predict the right blockage and the flow details close to the hub. At the part speed the computations without the shroud cavities fail to predict the major flow features in the passage and this leads to inaccurate predictions of massflow and shapes of the compressor characteristic. The paper demonstrates that an accurate representation of the endwall geometry and an effective turbulence model, together with a good quality and sufficiently refined grid result in a credible prediction of compressor matching and performance with steady state mixing planes.

AB - Computational Fluid Dynamics (CFD) has been widely used for compressor design, yet the prediction of performance and stage matching for multi-stage, high-speed machines remain challenging. This paper presents the authors' effort to improve the reliability of CFD in multistage compressor simulations. The endwall features (e.g. blade fillet and shape of the platform edge) are meshed with minimal approximations. Turbulence models with linear and non-linear eddy viscosity models are assessed. The non-linear eddy viscosity model predicts a higher production of turbulent kinetic energy in the passages, especially close to the endwall region. This results in a more accurate prediction of the choked mass flow and the shape of total pressure profiles close to the hub. The non-linear viscosity model generally shows an improvement on its linear counterparts based on the comparisons with the rig data. For geometrical details, truncated fillet leads to thicker boundary layer on the fillet and reduced mass flow and efficiency. Shroud cavities are found to be essential to predict the right blockage and the flow details close to the hub. At the part speed the computations without the shroud cavities fail to predict the major flow features in the passage and this leads to inaccurate predictions of massflow and shapes of the compressor characteristic. The paper demonstrates that an accurate representation of the endwall geometry and an effective turbulence model, together with a good quality and sufficiently refined grid result in a credible prediction of compressor matching and performance with steady state mixing planes.

UR - http://www.scopus.com/inward/record.url?scp=85028997386&partnerID=8YFLogxK

U2 - 10.1115/GT201764964

DO - 10.1115/GT201764964

M3 - Conference contribution

VL - 2A-2017

BT - Turbomachinery

PB - American Society of Mechanical Engineers (ASME)

ER -