Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor

Seishiro Saito, Masato Furukawa, Kazutoyo Yamada, Yuki Tamura, Akinori Matsuoka, Naoyuki Niwa

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

1 Citation (Scopus)

Abstract

In this study, the hub-corner separation in a multi-stage transonic axial compressor has been investigated using a largescale detached eddy simulation (DES) with about 4.5 hundred million computational cells. The complicated flow field near the hub wall in a stator with partial tip clearances was analyzed by data mining techniques extracting important flow phenomena from the DES results. The data mining techniques applied in the present study include vortex identification based on the critical point theory and topological data analysis of the limiting streamline pattern visualized by the line integral convolution (LIC) method. It is found from the time-averaged flow field in the first stator that the hub-corner separation vortex formed near the solid part of the stator tip interacts with the leakage flow and secondary flow on the hub wall, resulting in a complicated vortical flow field. Near the leading edge of the stator, the leakage flow from the front partial clearance generates the tip leakage vortex, which produces loss from the leading edge to 10 percent chord position. At the mid-chord, the hub-corner separation vortex suffers a breakdown, resulting in the widespread huge loss production. It is shown from limiting streamlines on the suction surface of the stator that a reverse flow region expands radially from the solid part of the stator tip toward the downstream. From 50 percent chord position to the trailing edge of the stator, the leakage flow through the rear partial clearance interacts with the secondary flow on the hub wall. The leakage vortex generated along the rear partial clearance becomes a major loss factor there.

Original languageEnglish
Title of host publicationSymposia
Subtitle of host publicationKeynotes; Advances in Numerical Modeling for Turbomachinery Flow Optimization; Fluid Machinery; Industrial and Environmental Applications of Fluid Mechanics; Pumping Machinery
PublisherAmerican Society of Mechanical Engineers (ASME)
Volume1A-2017
ISBN (Electronic)9780791858042
DOIs
Publication statusPublished - 2017
EventASME 2017 Fluids Engineering Division Summer Meeting, FEDSM 2017 - Waikoloa, United States
Duration: Jul 30 2017Aug 3 2017

Other

OtherASME 2017 Fluids Engineering Division Summer Meeting, FEDSM 2017
CountryUnited States
CityWaikoloa
Period7/30/178/3/17

Fingerprint

Flow structure
Stators
Compressors
Vortex flow
Flow fields
Secondary flow
Data mining
Convolution

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

Cite this

Saito, S., Furukawa, M., Yamada, K., Tamura, Y., Matsuoka, A., & Niwa, N. (2017). Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor. In Symposia: Keynotes; Advances in Numerical Modeling for Turbomachinery Flow Optimization; Fluid Machinery; Industrial and Environmental Applications of Fluid Mechanics; Pumping Machinery (Vol. 1A-2017). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/FEDSM2017-69116

Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor. / Saito, Seishiro; Furukawa, Masato; Yamada, Kazutoyo; Tamura, Yuki; Matsuoka, Akinori; Niwa, Naoyuki.

Symposia: Keynotes; Advances in Numerical Modeling for Turbomachinery Flow Optimization; Fluid Machinery; Industrial and Environmental Applications of Fluid Mechanics; Pumping Machinery. Vol. 1A-2017 American Society of Mechanical Engineers (ASME), 2017.

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

Saito, S, Furukawa, M, Yamada, K, Tamura, Y, Matsuoka, A & Niwa, N 2017, Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor. in Symposia: Keynotes; Advances in Numerical Modeling for Turbomachinery Flow Optimization; Fluid Machinery; Industrial and Environmental Applications of Fluid Mechanics; Pumping Machinery. vol. 1A-2017, American Society of Mechanical Engineers (ASME), ASME 2017 Fluids Engineering Division Summer Meeting, FEDSM 2017, Waikoloa, United States, 7/30/17. https://doi.org/10.1115/FEDSM2017-69116
Saito S, Furukawa M, Yamada K, Tamura Y, Matsuoka A, Niwa N. Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor. In Symposia: Keynotes; Advances in Numerical Modeling for Turbomachinery Flow Optimization; Fluid Machinery; Industrial and Environmental Applications of Fluid Mechanics; Pumping Machinery. Vol. 1A-2017. American Society of Mechanical Engineers (ASME). 2017 https://doi.org/10.1115/FEDSM2017-69116
Saito, Seishiro ; Furukawa, Masato ; Yamada, Kazutoyo ; Tamura, Yuki ; Matsuoka, Akinori ; Niwa, Naoyuki. / Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor. Symposia: Keynotes; Advances in Numerical Modeling for Turbomachinery Flow Optimization; Fluid Machinery; Industrial and Environmental Applications of Fluid Mechanics; Pumping Machinery. Vol. 1A-2017 American Society of Mechanical Engineers (ASME), 2017.
@inproceedings{557c113a95c7468e8e0c1ace7936020e,
title = "Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor",
abstract = "In this study, the hub-corner separation in a multi-stage transonic axial compressor has been investigated using a largescale detached eddy simulation (DES) with about 4.5 hundred million computational cells. The complicated flow field near the hub wall in a stator with partial tip clearances was analyzed by data mining techniques extracting important flow phenomena from the DES results. The data mining techniques applied in the present study include vortex identification based on the critical point theory and topological data analysis of the limiting streamline pattern visualized by the line integral convolution (LIC) method. It is found from the time-averaged flow field in the first stator that the hub-corner separation vortex formed near the solid part of the stator tip interacts with the leakage flow and secondary flow on the hub wall, resulting in a complicated vortical flow field. Near the leading edge of the stator, the leakage flow from the front partial clearance generates the tip leakage vortex, which produces loss from the leading edge to 10 percent chord position. At the mid-chord, the hub-corner separation vortex suffers a breakdown, resulting in the widespread huge loss production. It is shown from limiting streamlines on the suction surface of the stator that a reverse flow region expands radially from the solid part of the stator tip toward the downstream. From 50 percent chord position to the trailing edge of the stator, the leakage flow through the rear partial clearance interacts with the secondary flow on the hub wall. The leakage vortex generated along the rear partial clearance becomes a major loss factor there.",
author = "Seishiro Saito and Masato Furukawa and Kazutoyo Yamada and Yuki Tamura and Akinori Matsuoka and Naoyuki Niwa",
year = "2017",
doi = "10.1115/FEDSM2017-69116",
language = "English",
volume = "1A-2017",
booktitle = "Symposia",
publisher = "American Society of Mechanical Engineers (ASME)",

}

TY - GEN

T1 - Vortical flow structure of hub-corner separation in a stator cascade of a multi-stage transonic axial compressor

AU - Saito, Seishiro

AU - Furukawa, Masato

AU - Yamada, Kazutoyo

AU - Tamura, Yuki

AU - Matsuoka, Akinori

AU - Niwa, Naoyuki

PY - 2017

Y1 - 2017

N2 - In this study, the hub-corner separation in a multi-stage transonic axial compressor has been investigated using a largescale detached eddy simulation (DES) with about 4.5 hundred million computational cells. The complicated flow field near the hub wall in a stator with partial tip clearances was analyzed by data mining techniques extracting important flow phenomena from the DES results. The data mining techniques applied in the present study include vortex identification based on the critical point theory and topological data analysis of the limiting streamline pattern visualized by the line integral convolution (LIC) method. It is found from the time-averaged flow field in the first stator that the hub-corner separation vortex formed near the solid part of the stator tip interacts with the leakage flow and secondary flow on the hub wall, resulting in a complicated vortical flow field. Near the leading edge of the stator, the leakage flow from the front partial clearance generates the tip leakage vortex, which produces loss from the leading edge to 10 percent chord position. At the mid-chord, the hub-corner separation vortex suffers a breakdown, resulting in the widespread huge loss production. It is shown from limiting streamlines on the suction surface of the stator that a reverse flow region expands radially from the solid part of the stator tip toward the downstream. From 50 percent chord position to the trailing edge of the stator, the leakage flow through the rear partial clearance interacts with the secondary flow on the hub wall. The leakage vortex generated along the rear partial clearance becomes a major loss factor there.

AB - In this study, the hub-corner separation in a multi-stage transonic axial compressor has been investigated using a largescale detached eddy simulation (DES) with about 4.5 hundred million computational cells. The complicated flow field near the hub wall in a stator with partial tip clearances was analyzed by data mining techniques extracting important flow phenomena from the DES results. The data mining techniques applied in the present study include vortex identification based on the critical point theory and topological data analysis of the limiting streamline pattern visualized by the line integral convolution (LIC) method. It is found from the time-averaged flow field in the first stator that the hub-corner separation vortex formed near the solid part of the stator tip interacts with the leakage flow and secondary flow on the hub wall, resulting in a complicated vortical flow field. Near the leading edge of the stator, the leakage flow from the front partial clearance generates the tip leakage vortex, which produces loss from the leading edge to 10 percent chord position. At the mid-chord, the hub-corner separation vortex suffers a breakdown, resulting in the widespread huge loss production. It is shown from limiting streamlines on the suction surface of the stator that a reverse flow region expands radially from the solid part of the stator tip toward the downstream. From 50 percent chord position to the trailing edge of the stator, the leakage flow through the rear partial clearance interacts with the secondary flow on the hub wall. The leakage vortex generated along the rear partial clearance becomes a major loss factor there.

UR - http://www.scopus.com/inward/record.url?scp=85033571964&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=85033571964&partnerID=8YFLogxK

U2 - 10.1115/FEDSM2017-69116

DO - 10.1115/FEDSM2017-69116

M3 - Conference contribution

AN - SCOPUS:85033571964

VL - 1A-2017

BT - Symposia

PB - American Society of Mechanical Engineers (ASME)

ER -