The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor

K. Yamada, K. Funazaki, M. Furukawa

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

42 Citations (Scopus)

Abstract

It is known that the tip clearance flow is dominant and very important flow phenomena in axial compressor aerodynamics because the tip clearance flow has a great influence on the stability as well as aerodynamic loss of compressors. Our goal is to clarify the behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor (NASA Rotor 37). In the present work, steady and unsteady RANS simulations were performed to investigate vortical flow structures and separated flow field near the tip for several different clearance cases. Boundary layer separation on the casing wall and blade suction surface was investigated in detail for near-stall and stall condition. In order to understand such complicated flow field, vortex cores were identified using the critical point theory and a topology of the three-dimensional separated and vortical flows was analyzed. In the nominal clearance case, the breakdown of tip leakage vortex has occurred at a near-stall operating condition because of the interaction of the vortex with the shock wave, leading to a large blockage and unsteadiness in the rotor tip. On the other hand, the calculation with no clearance suggested that the separation on the suction surface was different from that with the nominal clearance. Since the shock wave induced the boundary layer separation on the blade suction surface in the transonic axial compressor rotor, focal-type critical points appeared on the suction surface near the tip at near-stall condition.

Original languageEnglish
Title of host publicationProceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air
Pages295-306
Number of pages12
DOIs
Publication statusPublished - Sep 25 2007
Event2007 ASME Turbo Expo - Montreal, Que., Canada
Duration: May 14 2007May 17 2007

Publication series

NameProceedings of the ASME Turbo Expo
Volume6 PART A

Other

Other2007 ASME Turbo Expo
CountryCanada
CityMontreal, Que.
Period5/14/075/17/07

Fingerprint

Compressors
Rotors
Vortex flow
Shock waves
Flow fields
Boundary layers
Aerodynamic stability
Flow structure
Turbomachine blades
NASA
Aerodynamics
Topology

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Yamada, K., Funazaki, K., & Furukawa, M. (2007). The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor. In Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air (pp. 295-306). (Proceedings of the ASME Turbo Expo; Vol. 6 PART A). https://doi.org/10.1115/GT2007-27725

The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor. / Yamada, K.; Funazaki, K.; Furukawa, M.

Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. 2007. p. 295-306 (Proceedings of the ASME Turbo Expo; Vol. 6 PART A).

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

Yamada, K, Funazaki, K & Furukawa, M 2007, The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor. in Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. Proceedings of the ASME Turbo Expo, vol. 6 PART A, pp. 295-306, 2007 ASME Turbo Expo, Montreal, Que., Canada, 5/14/07. https://doi.org/10.1115/GT2007-27725
Yamada K, Funazaki K, Furukawa M. The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor. In Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. 2007. p. 295-306. (Proceedings of the ASME Turbo Expo). https://doi.org/10.1115/GT2007-27725
Yamada, K. ; Funazaki, K. ; Furukawa, M. / The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor. Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air. 2007. pp. 295-306 (Proceedings of the ASME Turbo Expo).
@inproceedings{5f6b1dd6448c402aa51f34f6a4ca7b06,
title = "The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor",
abstract = "It is known that the tip clearance flow is dominant and very important flow phenomena in axial compressor aerodynamics because the tip clearance flow has a great influence on the stability as well as aerodynamic loss of compressors. Our goal is to clarify the behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor (NASA Rotor 37). In the present work, steady and unsteady RANS simulations were performed to investigate vortical flow structures and separated flow field near the tip for several different clearance cases. Boundary layer separation on the casing wall and blade suction surface was investigated in detail for near-stall and stall condition. In order to understand such complicated flow field, vortex cores were identified using the critical point theory and a topology of the three-dimensional separated and vortical flows was analyzed. In the nominal clearance case, the breakdown of tip leakage vortex has occurred at a near-stall operating condition because of the interaction of the vortex with the shock wave, leading to a large blockage and unsteadiness in the rotor tip. On the other hand, the calculation with no clearance suggested that the separation on the suction surface was different from that with the nominal clearance. Since the shock wave induced the boundary layer separation on the blade suction surface in the transonic axial compressor rotor, focal-type critical points appeared on the suction surface near the tip at near-stall condition.",
author = "K. Yamada and K. Funazaki and M. Furukawa",
year = "2007",
month = "9",
day = "25",
doi = "10.1115/GT2007-27725",
language = "English",
isbn = "079184790X",
series = "Proceedings of the ASME Turbo Expo",
pages = "295--306",
booktitle = "Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air",

}

TY - GEN

T1 - The behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor

AU - Yamada, K.

AU - Funazaki, K.

AU - Furukawa, M.

PY - 2007/9/25

Y1 - 2007/9/25

N2 - It is known that the tip clearance flow is dominant and very important flow phenomena in axial compressor aerodynamics because the tip clearance flow has a great influence on the stability as well as aerodynamic loss of compressors. Our goal is to clarify the behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor (NASA Rotor 37). In the present work, steady and unsteady RANS simulations were performed to investigate vortical flow structures and separated flow field near the tip for several different clearance cases. Boundary layer separation on the casing wall and blade suction surface was investigated in detail for near-stall and stall condition. In order to understand such complicated flow field, vortex cores were identified using the critical point theory and a topology of the three-dimensional separated and vortical flows was analyzed. In the nominal clearance case, the breakdown of tip leakage vortex has occurred at a near-stall operating condition because of the interaction of the vortex with the shock wave, leading to a large blockage and unsteadiness in the rotor tip. On the other hand, the calculation with no clearance suggested that the separation on the suction surface was different from that with the nominal clearance. Since the shock wave induced the boundary layer separation on the blade suction surface in the transonic axial compressor rotor, focal-type critical points appeared on the suction surface near the tip at near-stall condition.

AB - It is known that the tip clearance flow is dominant and very important flow phenomena in axial compressor aerodynamics because the tip clearance flow has a great influence on the stability as well as aerodynamic loss of compressors. Our goal is to clarify the behavior of tip clearance flow at near-stall condition in a transonic axial compressor rotor (NASA Rotor 37). In the present work, steady and unsteady RANS simulations were performed to investigate vortical flow structures and separated flow field near the tip for several different clearance cases. Boundary layer separation on the casing wall and blade suction surface was investigated in detail for near-stall and stall condition. In order to understand such complicated flow field, vortex cores were identified using the critical point theory and a topology of the three-dimensional separated and vortical flows was analyzed. In the nominal clearance case, the breakdown of tip leakage vortex has occurred at a near-stall operating condition because of the interaction of the vortex with the shock wave, leading to a large blockage and unsteadiness in the rotor tip. On the other hand, the calculation with no clearance suggested that the separation on the suction surface was different from that with the nominal clearance. Since the shock wave induced the boundary layer separation on the blade suction surface in the transonic axial compressor rotor, focal-type critical points appeared on the suction surface near the tip at near-stall condition.

UR - http://www.scopus.com/inward/record.url?scp=34548749309&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=34548749309&partnerID=8YFLogxK

U2 - 10.1115/GT2007-27725

DO - 10.1115/GT2007-27725

M3 - Conference contribution

AN - SCOPUS:34548749309

SN - 079184790X

SN - 9780791847909

T3 - Proceedings of the ASME Turbo Expo

SP - 295

EP - 306

BT - Proceedings of the ASME Turbo Expo 2007 - Power for Land, Sea, and Air

ER -