Large-scale des analysis of unsteady flow field in a multi-stage axial flow compreßor at off-design condition using k computer

Kazutoyo Yamada, Masato Furukawa, Satoshi Nakakido, Akinori Matsuoka, Kentaro Nakayama

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

9 Citations (Scopus)

Abstract

The paper presents the results of large-scale numerical simulations which were conducted for better understanding of unsteady flow phenomena in a multi-stage axial flow compreßor at off-design condition. The compreßor is a test rig compreßor which was used for development of the industrial gas turbine, Kawasaki L30A. The compreßor consists of 14 stages, the front two stages and the front half stages of which were investigated in the present study. The final goal of this study is to elucidate the flow mechanism of the rotating stall inception in the multi-stage axial compreßor for actual gas turbines, and according to the test data it is considered that the 2nd stage and the 5th or 6th stage are suspected of leading to the stall. In order to capture precise flow physics in the compreßor, a computational mesh for the simulation was generated to have at least several million cells per paßage, which amounted to 650 million cells for the front 2-stage simulation and two billion cells for the front 7-stage simulation (about three hundred million cells for each stage). Since these were still not enough for the largeeddy simulation (LES), the detached-eddy simulation (DES) was employed, which can calculate flow fields except near-wall region by LES. The required computational resources were quite large for such simulations, so the computations were conducted on the K computer (RIKEN AICS in Japan). The simulations were well validated, showing good agreement with the measurement results obtained in the test. In the validation, the effect of the boundary condition for the casing wall was also investigated by comparing the results between the adiabatic boundary condition and the isothermal boundary condition. As for the unsteady effect, the wake/blade interaction was investigated in detail. In addition, unsteady flow phenomena in the present compreßor at off-design condition were analyzed by using data mining techniques such as vortex identification and limiting streamline drawing with the LIC (line integral convolution) method. The simulation showed that they could be caused by the corner separation on the hub side.

Original languageEnglish
Title of host publicationTurbomachinery
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791856659, 9780791856659
DOIs
Publication statusPublished - Jan 1 2015
EventASME Turbo Expo 2015: Turbine Technical Conference and Exposition, GT 2015 - Montreal, Canada
Duration: Jun 15 2015Jun 19 2015

Publication series

NameProceedings of the ASME Turbo Expo
Volume2C

Other

OtherASME Turbo Expo 2015: Turbine Technical Conference and Exposition, GT 2015
CountryCanada
CityMontreal
Period6/15/156/19/15

Fingerprint

Axial flow
Unsteady flow
Flow fields
Boundary conditions
Gas turbines
Convolution
Data mining
Vortex flow
Physics
Computer simulation

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Yamada, K., Furukawa, M., Nakakido, S., Matsuoka, A., & Nakayama, K. (2015). Large-scale des analysis of unsteady flow field in a multi-stage axial flow compreßor at off-design condition using k computer. In Turbomachinery (Proceedings of the ASME Turbo Expo; Vol. 2C). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/GT2015-42648

Large-scale des analysis of unsteady flow field in a multi-stage axial flow compreßor at off-design condition using k computer. / Yamada, Kazutoyo; Furukawa, Masato; Nakakido, Satoshi; Matsuoka, Akinori; Nakayama, Kentaro.

Turbomachinery. American Society of Mechanical Engineers (ASME), 2015. (Proceedings of the ASME Turbo Expo; Vol. 2C).

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

Yamada, K, Furukawa, M, Nakakido, S, Matsuoka, A & Nakayama, K 2015, Large-scale des analysis of unsteady flow field in a multi-stage axial flow compreßor at off-design condition using k computer. in Turbomachinery. Proceedings of the ASME Turbo Expo, vol. 2C, American Society of Mechanical Engineers (ASME), ASME Turbo Expo 2015: Turbine Technical Conference and Exposition, GT 2015, Montreal, Canada, 6/15/15. https://doi.org/10.1115/GT2015-42648
Yamada K, Furukawa M, Nakakido S, Matsuoka A, Nakayama K. Large-scale des analysis of unsteady flow field in a multi-stage axial flow compreßor at off-design condition using k computer. In Turbomachinery. American Society of Mechanical Engineers (ASME). 2015. (Proceedings of the ASME Turbo Expo). https://doi.org/10.1115/GT2015-42648
Yamada, Kazutoyo ; Furukawa, Masato ; Nakakido, Satoshi ; Matsuoka, Akinori ; Nakayama, Kentaro. / Large-scale des analysis of unsteady flow field in a multi-stage axial flow compreßor at off-design condition using k computer. Turbomachinery. American Society of Mechanical Engineers (ASME), 2015. (Proceedings of the ASME Turbo Expo).
@inproceedings{58ab858562ce4340980c236b41785027,
title = "Large-scale des analysis of unsteady flow field in a multi-stage axial flow compre{\ss}or at off-design condition using k computer",
abstract = "The paper presents the results of large-scale numerical simulations which were conducted for better understanding of unsteady flow phenomena in a multi-stage axial flow compre{\ss}or at off-design condition. The compre{\ss}or is a test rig compre{\ss}or which was used for development of the industrial gas turbine, Kawasaki L30A. The compre{\ss}or consists of 14 stages, the front two stages and the front half stages of which were investigated in the present study. The final goal of this study is to elucidate the flow mechanism of the rotating stall inception in the multi-stage axial compre{\ss}or for actual gas turbines, and according to the test data it is considered that the 2nd stage and the 5th or 6th stage are suspected of leading to the stall. In order to capture precise flow physics in the compre{\ss}or, a computational mesh for the simulation was generated to have at least several million cells per pa{\ss}age, which amounted to 650 million cells for the front 2-stage simulation and two billion cells for the front 7-stage simulation (about three hundred million cells for each stage). Since these were still not enough for the largeeddy simulation (LES), the detached-eddy simulation (DES) was employed, which can calculate flow fields except near-wall region by LES. The required computational resources were quite large for such simulations, so the computations were conducted on the K computer (RIKEN AICS in Japan). The simulations were well validated, showing good agreement with the measurement results obtained in the test. In the validation, the effect of the boundary condition for the casing wall was also investigated by comparing the results between the adiabatic boundary condition and the isothermal boundary condition. As for the unsteady effect, the wake/blade interaction was investigated in detail. In addition, unsteady flow phenomena in the present compre{\ss}or at off-design condition were analyzed by using data mining techniques such as vortex identification and limiting streamline drawing with the LIC (line integral convolution) method. The simulation showed that they could be caused by the corner separation on the hub side.",
author = "Kazutoyo Yamada and Masato Furukawa and Satoshi Nakakido and Akinori Matsuoka and Kentaro Nakayama",
year = "2015",
month = "1",
day = "1",
doi = "10.1115/GT2015-42648",
language = "English",
series = "Proceedings of the ASME Turbo Expo",
publisher = "American Society of Mechanical Engineers (ASME)",
booktitle = "Turbomachinery",

}

TY - GEN

T1 - Large-scale des analysis of unsteady flow field in a multi-stage axial flow compreßor at off-design condition using k computer

AU - Yamada, Kazutoyo

AU - Furukawa, Masato

AU - Nakakido, Satoshi

AU - Matsuoka, Akinori

AU - Nakayama, Kentaro

PY - 2015/1/1

Y1 - 2015/1/1

N2 - The paper presents the results of large-scale numerical simulations which were conducted for better understanding of unsteady flow phenomena in a multi-stage axial flow compreßor at off-design condition. The compreßor is a test rig compreßor which was used for development of the industrial gas turbine, Kawasaki L30A. The compreßor consists of 14 stages, the front two stages and the front half stages of which were investigated in the present study. The final goal of this study is to elucidate the flow mechanism of the rotating stall inception in the multi-stage axial compreßor for actual gas turbines, and according to the test data it is considered that the 2nd stage and the 5th or 6th stage are suspected of leading to the stall. In order to capture precise flow physics in the compreßor, a computational mesh for the simulation was generated to have at least several million cells per paßage, which amounted to 650 million cells for the front 2-stage simulation and two billion cells for the front 7-stage simulation (about three hundred million cells for each stage). Since these were still not enough for the largeeddy simulation (LES), the detached-eddy simulation (DES) was employed, which can calculate flow fields except near-wall region by LES. The required computational resources were quite large for such simulations, so the computations were conducted on the K computer (RIKEN AICS in Japan). The simulations were well validated, showing good agreement with the measurement results obtained in the test. In the validation, the effect of the boundary condition for the casing wall was also investigated by comparing the results between the adiabatic boundary condition and the isothermal boundary condition. As for the unsteady effect, the wake/blade interaction was investigated in detail. In addition, unsteady flow phenomena in the present compreßor at off-design condition were analyzed by using data mining techniques such as vortex identification and limiting streamline drawing with the LIC (line integral convolution) method. The simulation showed that they could be caused by the corner separation on the hub side.

AB - The paper presents the results of large-scale numerical simulations which were conducted for better understanding of unsteady flow phenomena in a multi-stage axial flow compreßor at off-design condition. The compreßor is a test rig compreßor which was used for development of the industrial gas turbine, Kawasaki L30A. The compreßor consists of 14 stages, the front two stages and the front half stages of which were investigated in the present study. The final goal of this study is to elucidate the flow mechanism of the rotating stall inception in the multi-stage axial compreßor for actual gas turbines, and according to the test data it is considered that the 2nd stage and the 5th or 6th stage are suspected of leading to the stall. In order to capture precise flow physics in the compreßor, a computational mesh for the simulation was generated to have at least several million cells per paßage, which amounted to 650 million cells for the front 2-stage simulation and two billion cells for the front 7-stage simulation (about three hundred million cells for each stage). Since these were still not enough for the largeeddy simulation (LES), the detached-eddy simulation (DES) was employed, which can calculate flow fields except near-wall region by LES. The required computational resources were quite large for such simulations, so the computations were conducted on the K computer (RIKEN AICS in Japan). The simulations were well validated, showing good agreement with the measurement results obtained in the test. In the validation, the effect of the boundary condition for the casing wall was also investigated by comparing the results between the adiabatic boundary condition and the isothermal boundary condition. As for the unsteady effect, the wake/blade interaction was investigated in detail. In addition, unsteady flow phenomena in the present compreßor at off-design condition were analyzed by using data mining techniques such as vortex identification and limiting streamline drawing with the LIC (line integral convolution) method. The simulation showed that they could be caused by the corner separation on the hub side.

UR - http://www.scopus.com/inward/record.url?scp=84954103020&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84954103020&partnerID=8YFLogxK

U2 - 10.1115/GT2015-42648

DO - 10.1115/GT2015-42648

M3 - Conference contribution

AN - SCOPUS:84954103020

T3 - Proceedings of the ASME Turbo Expo

BT - Turbomachinery

PB - American Society of Mechanical Engineers (ASME)

ER -