Large-scale des analysis of stall inception process in a multi-stage axial flow compressor

Kazutoyo Yamada, Masato Furukawa, Yuki Tamura, Seishiro Saito, Akinori Matsuoka, Kentaro Nakayama

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

2 Citations (Scopus)

Abstract

The paper describes the flow mechanism of the rotating stall inception in a multi-stage axial flow compressor for an actual gas turbine. Large-scale numerical simulations have been conducted. The compressor investigated is a test rig compressor which was used for development of the industrial gas turbine, Kawasaki L30A. While the compressor consists of 14 stages, the front half stages of the compressor were analyzed in the present study. According to the test data, it is considered that the 5th or 6th stage is the one most suspected of leading to the stall. In order to capture precise flow physics that could happen at stall inception, a computational mesh was made dense, giving at least several million cells to each passage. It amounted to about two billion cells for the first 7 stages (three hundred million cells in each stage). Since the mesh was still not enough for the largeeddy simulation (LES), the detached-eddy simulation (DES) was employed. In the DES, a flow field is calculated by LES except near-wall and near-wall turbulent eddies are modeled by RANS. The computational resource required for such large-scale simulation was still quite large, so the computations were conducted on the K computer (RIKEN AICS in Japan). Unsteady flow phenomena at the stall inception were analyzed by using data mining techniques such as vortex identification and limiting streamline drawing with the LIC (line integral convolution) method. The present compressor has stall started from the separation on the hub side instead of the commonly observed leading-edge separation near the tip. The flow phenomenon first observed in the stalling process is the hub corner separation, which appears in some passage of the 6th stator when approaching the stall point. This hub corner separation expands with time, and eventually leads to the leading-edge separation on the hub side for the stator. Once the leading-edge separation happens, it rapidly develops into the rotating stall, causing another leading-edge separation for the neighboring blade in sequence. Finally, the rotating stall spreads to the upstream and downstream bladerows due to its large blockage effect.

Original languageEnglish
Title of host publicationTurbomachinery
PublisherAmerican Society of Mechanical Engineers (ASME)
Volume2D-2016
ISBN (Electronic)9780791849729
DOIs
Publication statusPublished - Jan 1 2016
EventASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, GT 2016 - Seoul, Korea, Republic of
Duration: Jun 13 2016Jun 17 2016

Other

OtherASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, GT 2016
CountryKorea, Republic of
CitySeoul
Period6/13/166/17/16

Fingerprint

Axial-flow compressors
Compressors
Stators
Gas turbines
Unsteady flow
Convolution
Data mining
Flow fields
Vortex flow
Physics
Computer simulation

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Yamada, K., Furukawa, M., Tamura, Y., Saito, S., Matsuoka, A., & Nakayama, K. (2016). Large-scale des analysis of stall inception process in a multi-stage axial flow compressor. In Turbomachinery (Vol. 2D-2016). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/GT2016-57104

Large-scale des analysis of stall inception process in a multi-stage axial flow compressor. / Yamada, Kazutoyo; Furukawa, Masato; Tamura, Yuki; Saito, Seishiro; Matsuoka, Akinori; Nakayama, Kentaro.

Turbomachinery. Vol. 2D-2016 American Society of Mechanical Engineers (ASME), 2016.

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

Yamada, K, Furukawa, M, Tamura, Y, Saito, S, Matsuoka, A & Nakayama, K 2016, Large-scale des analysis of stall inception process in a multi-stage axial flow compressor. in Turbomachinery. vol. 2D-2016, American Society of Mechanical Engineers (ASME), ASME Turbo Expo 2016: Turbomachinery Technical Conference and Exposition, GT 2016, Seoul, Korea, Republic of, 6/13/16. https://doi.org/10.1115/GT2016-57104
Yamada K, Furukawa M, Tamura Y, Saito S, Matsuoka A, Nakayama K. Large-scale des analysis of stall inception process in a multi-stage axial flow compressor. In Turbomachinery. Vol. 2D-2016. American Society of Mechanical Engineers (ASME). 2016 https://doi.org/10.1115/GT2016-57104
Yamada, Kazutoyo ; Furukawa, Masato ; Tamura, Yuki ; Saito, Seishiro ; Matsuoka, Akinori ; Nakayama, Kentaro. / Large-scale des analysis of stall inception process in a multi-stage axial flow compressor. Turbomachinery. Vol. 2D-2016 American Society of Mechanical Engineers (ASME), 2016.
@inproceedings{4cc624e7148a47e585450c85a96dd18c,
title = "Large-scale des analysis of stall inception process in a multi-stage axial flow compressor",
abstract = "The paper describes the flow mechanism of the rotating stall inception in a multi-stage axial flow compressor for an actual gas turbine. Large-scale numerical simulations have been conducted. The compressor investigated is a test rig compressor which was used for development of the industrial gas turbine, Kawasaki L30A. While the compressor consists of 14 stages, the front half stages of the compressor were analyzed in the present study. According to the test data, it is considered that the 5th or 6th stage is the one most suspected of leading to the stall. In order to capture precise flow physics that could happen at stall inception, a computational mesh was made dense, giving at least several million cells to each passage. It amounted to about two billion cells for the first 7 stages (three hundred million cells in each stage). Since the mesh was still not enough for the largeeddy simulation (LES), the detached-eddy simulation (DES) was employed. In the DES, a flow field is calculated by LES except near-wall and near-wall turbulent eddies are modeled by RANS. The computational resource required for such large-scale simulation was still quite large, so the computations were conducted on the K computer (RIKEN AICS in Japan). Unsteady flow phenomena at the stall inception were analyzed by using data mining techniques such as vortex identification and limiting streamline drawing with the LIC (line integral convolution) method. The present compressor has stall started from the separation on the hub side instead of the commonly observed leading-edge separation near the tip. The flow phenomenon first observed in the stalling process is the hub corner separation, which appears in some passage of the 6th stator when approaching the stall point. This hub corner separation expands with time, and eventually leads to the leading-edge separation on the hub side for the stator. Once the leading-edge separation happens, it rapidly develops into the rotating stall, causing another leading-edge separation for the neighboring blade in sequence. Finally, the rotating stall spreads to the upstream and downstream bladerows due to its large blockage effect.",
author = "Kazutoyo Yamada and Masato Furukawa and Yuki Tamura and Seishiro Saito and Akinori Matsuoka and Kentaro Nakayama",
year = "2016",
month = "1",
day = "1",
doi = "10.1115/GT2016-57104",
language = "English",
volume = "2D-2016",
booktitle = "Turbomachinery",
publisher = "American Society of Mechanical Engineers (ASME)",

}

TY - GEN

T1 - Large-scale des analysis of stall inception process in a multi-stage axial flow compressor

AU - Yamada, Kazutoyo

AU - Furukawa, Masato

AU - Tamura, Yuki

AU - Saito, Seishiro

AU - Matsuoka, Akinori

AU - Nakayama, Kentaro

PY - 2016/1/1

Y1 - 2016/1/1

N2 - The paper describes the flow mechanism of the rotating stall inception in a multi-stage axial flow compressor for an actual gas turbine. Large-scale numerical simulations have been conducted. The compressor investigated is a test rig compressor which was used for development of the industrial gas turbine, Kawasaki L30A. While the compressor consists of 14 stages, the front half stages of the compressor were analyzed in the present study. According to the test data, it is considered that the 5th or 6th stage is the one most suspected of leading to the stall. In order to capture precise flow physics that could happen at stall inception, a computational mesh was made dense, giving at least several million cells to each passage. It amounted to about two billion cells for the first 7 stages (three hundred million cells in each stage). Since the mesh was still not enough for the largeeddy simulation (LES), the detached-eddy simulation (DES) was employed. In the DES, a flow field is calculated by LES except near-wall and near-wall turbulent eddies are modeled by RANS. The computational resource required for such large-scale simulation was still quite large, so the computations were conducted on the K computer (RIKEN AICS in Japan). Unsteady flow phenomena at the stall inception were analyzed by using data mining techniques such as vortex identification and limiting streamline drawing with the LIC (line integral convolution) method. The present compressor has stall started from the separation on the hub side instead of the commonly observed leading-edge separation near the tip. The flow phenomenon first observed in the stalling process is the hub corner separation, which appears in some passage of the 6th stator when approaching the stall point. This hub corner separation expands with time, and eventually leads to the leading-edge separation on the hub side for the stator. Once the leading-edge separation happens, it rapidly develops into the rotating stall, causing another leading-edge separation for the neighboring blade in sequence. Finally, the rotating stall spreads to the upstream and downstream bladerows due to its large blockage effect.

AB - The paper describes the flow mechanism of the rotating stall inception in a multi-stage axial flow compressor for an actual gas turbine. Large-scale numerical simulations have been conducted. The compressor investigated is a test rig compressor which was used for development of the industrial gas turbine, Kawasaki L30A. While the compressor consists of 14 stages, the front half stages of the compressor were analyzed in the present study. According to the test data, it is considered that the 5th or 6th stage is the one most suspected of leading to the stall. In order to capture precise flow physics that could happen at stall inception, a computational mesh was made dense, giving at least several million cells to each passage. It amounted to about two billion cells for the first 7 stages (three hundred million cells in each stage). Since the mesh was still not enough for the largeeddy simulation (LES), the detached-eddy simulation (DES) was employed. In the DES, a flow field is calculated by LES except near-wall and near-wall turbulent eddies are modeled by RANS. The computational resource required for such large-scale simulation was still quite large, so the computations were conducted on the K computer (RIKEN AICS in Japan). Unsteady flow phenomena at the stall inception were analyzed by using data mining techniques such as vortex identification and limiting streamline drawing with the LIC (line integral convolution) method. The present compressor has stall started from the separation on the hub side instead of the commonly observed leading-edge separation near the tip. The flow phenomenon first observed in the stalling process is the hub corner separation, which appears in some passage of the 6th stator when approaching the stall point. This hub corner separation expands with time, and eventually leads to the leading-edge separation on the hub side for the stator. Once the leading-edge separation happens, it rapidly develops into the rotating stall, causing another leading-edge separation for the neighboring blade in sequence. Finally, the rotating stall spreads to the upstream and downstream bladerows due to its large blockage effect.

UR - http://www.scopus.com/inward/record.url?scp=84991717289&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84991717289&partnerID=8YFLogxK

U2 - 10.1115/GT2016-57104

DO - 10.1115/GT2016-57104

M3 - Conference contribution

AN - SCOPUS:84991717289

VL - 2D-2016

BT - Turbomachinery

PB - American Society of Mechanical Engineers (ASME)

ER -