Controlled-endwall-flow blading for multistage axial compressor rotor

M. Inoue, M. Kuroumaru, Masato Furukawa, Y. Kinoue, T. Tanino, S. Maeda, K. Okuno

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

5 Citations (Scopus)

Abstract

This research aims to develop an advanced technology of highly loaded axial compressor stages with high efficiency and sufficient surge margin. To improve endwall boundary layer flows which lead to energy loss and instability at an operation of low flow rate, the Controlled-Endwall-Flow (CEF) rotor blades were designed and tested in the low speed rotating cascade facility of Kyushu University. The CEF rotor blades have three distinctive features: The leading-edge sweep near hub and casing wall, the leading-edge bend near the casing, and the same exit metal angle of blade evaluated by a conventional design method. Mechanical strength of the blade was verified by a numerical simulation at a high speed condition. The baseline rotor blades were designed under the same design condition and tested to compare with the CEF rotor. The results showed that. the maximum stage efficiency of the CEF rotor was higher by 0.7 percent and the increase in surge margin was more than 20 percent in comparison with the baseline rotor. The results of both internal flow survey and 3D Navier-Stokes analysis showed that improvement of the overall stage performance resulted from activation of the endwall boundary layers, and suggested that further improvement might be expected by combination of end-bend stator blades and a highly loaded axial compressor stage could be developed by use of the CEF rotor.

Original languageEnglish
Title of host publicationAircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery
PublisherAmerican Society of Mechanical Engineers (ASME)
ISBN (Electronic)9780791878682
DOIs
Publication statusPublished - Jan 1 1997
EventASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1997 - Orlando, United States
Duration: Jun 2 1997Jun 5 1997

Publication series

NameProceedings of the ASME Turbo Expo
Volume1

Other

OtherASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1997
CountryUnited States
CityOrlando
Period6/2/976/5/97

Fingerprint

Compressors
Rotors
Turbomachine blades
Cascades (fluid mechanics)
Boundary layer flow
Stators
Strength of materials
Energy dissipation
Boundary layers
Chemical activation
Flow rate
Computer simulation
Metals

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Inoue, M., Kuroumaru, M., Furukawa, M., Kinoue, Y., Tanino, T., Maeda, S., & Okuno, K. (1997). Controlled-endwall-flow blading for multistage axial compressor rotor. In Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery (Proceedings of the ASME Turbo Expo; Vol. 1). American Society of Mechanical Engineers (ASME). https://doi.org/10.1115/97-GT-248

Controlled-endwall-flow blading for multistage axial compressor rotor. / Inoue, M.; Kuroumaru, M.; Furukawa, Masato; Kinoue, Y.; Tanino, T.; Maeda, S.; Okuno, K.

Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. American Society of Mechanical Engineers (ASME), 1997. (Proceedings of the ASME Turbo Expo; Vol. 1).

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

Inoue, M, Kuroumaru, M, Furukawa, M, Kinoue, Y, Tanino, T, Maeda, S & Okuno, K 1997, Controlled-endwall-flow blading for multistage axial compressor rotor. in Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. Proceedings of the ASME Turbo Expo, vol. 1, American Society of Mechanical Engineers (ASME), ASME 1997 International Gas Turbine and Aeroengine Congress and Exhibition, GT 1997, Orlando, United States, 6/2/97. https://doi.org/10.1115/97-GT-248
Inoue M, Kuroumaru M, Furukawa M, Kinoue Y, Tanino T, Maeda S et al. Controlled-endwall-flow blading for multistage axial compressor rotor. In Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. American Society of Mechanical Engineers (ASME). 1997. (Proceedings of the ASME Turbo Expo). https://doi.org/10.1115/97-GT-248
Inoue, M. ; Kuroumaru, M. ; Furukawa, Masato ; Kinoue, Y. ; Tanino, T. ; Maeda, S. ; Okuno, K. / Controlled-endwall-flow blading for multistage axial compressor rotor. Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery. American Society of Mechanical Engineers (ASME), 1997. (Proceedings of the ASME Turbo Expo).
@inproceedings{f6cc7027e36e4477bb0f0c76f7888938,
title = "Controlled-endwall-flow blading for multistage axial compressor rotor",
abstract = "This research aims to develop an advanced technology of highly loaded axial compressor stages with high efficiency and sufficient surge margin. To improve endwall boundary layer flows which lead to energy loss and instability at an operation of low flow rate, the Controlled-Endwall-Flow (CEF) rotor blades were designed and tested in the low speed rotating cascade facility of Kyushu University. The CEF rotor blades have three distinctive features: The leading-edge sweep near hub and casing wall, the leading-edge bend near the casing, and the same exit metal angle of blade evaluated by a conventional design method. Mechanical strength of the blade was verified by a numerical simulation at a high speed condition. The baseline rotor blades were designed under the same design condition and tested to compare with the CEF rotor. The results showed that. the maximum stage efficiency of the CEF rotor was higher by 0.7 percent and the increase in surge margin was more than 20 percent in comparison with the baseline rotor. The results of both internal flow survey and 3D Navier-Stokes analysis showed that improvement of the overall stage performance resulted from activation of the endwall boundary layers, and suggested that further improvement might be expected by combination of end-bend stator blades and a highly loaded axial compressor stage could be developed by use of the CEF rotor.",
author = "M. Inoue and M. Kuroumaru and Masato Furukawa and Y. Kinoue and T. Tanino and S. Maeda and K. Okuno",
year = "1997",
month = "1",
day = "1",
doi = "10.1115/97-GT-248",
language = "English",
series = "Proceedings of the ASME Turbo Expo",
publisher = "American Society of Mechanical Engineers (ASME)",
booktitle = "Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery",

}

TY - GEN

T1 - Controlled-endwall-flow blading for multistage axial compressor rotor

AU - Inoue, M.

AU - Kuroumaru, M.

AU - Furukawa, Masato

AU - Kinoue, Y.

AU - Tanino, T.

AU - Maeda, S.

AU - Okuno, K.

PY - 1997/1/1

Y1 - 1997/1/1

N2 - This research aims to develop an advanced technology of highly loaded axial compressor stages with high efficiency and sufficient surge margin. To improve endwall boundary layer flows which lead to energy loss and instability at an operation of low flow rate, the Controlled-Endwall-Flow (CEF) rotor blades were designed and tested in the low speed rotating cascade facility of Kyushu University. The CEF rotor blades have three distinctive features: The leading-edge sweep near hub and casing wall, the leading-edge bend near the casing, and the same exit metal angle of blade evaluated by a conventional design method. Mechanical strength of the blade was verified by a numerical simulation at a high speed condition. The baseline rotor blades were designed under the same design condition and tested to compare with the CEF rotor. The results showed that. the maximum stage efficiency of the CEF rotor was higher by 0.7 percent and the increase in surge margin was more than 20 percent in comparison with the baseline rotor. The results of both internal flow survey and 3D Navier-Stokes analysis showed that improvement of the overall stage performance resulted from activation of the endwall boundary layers, and suggested that further improvement might be expected by combination of end-bend stator blades and a highly loaded axial compressor stage could be developed by use of the CEF rotor.

AB - This research aims to develop an advanced technology of highly loaded axial compressor stages with high efficiency and sufficient surge margin. To improve endwall boundary layer flows which lead to energy loss and instability at an operation of low flow rate, the Controlled-Endwall-Flow (CEF) rotor blades were designed and tested in the low speed rotating cascade facility of Kyushu University. The CEF rotor blades have three distinctive features: The leading-edge sweep near hub and casing wall, the leading-edge bend near the casing, and the same exit metal angle of blade evaluated by a conventional design method. Mechanical strength of the blade was verified by a numerical simulation at a high speed condition. The baseline rotor blades were designed under the same design condition and tested to compare with the CEF rotor. The results showed that. the maximum stage efficiency of the CEF rotor was higher by 0.7 percent and the increase in surge margin was more than 20 percent in comparison with the baseline rotor. The results of both internal flow survey and 3D Navier-Stokes analysis showed that improvement of the overall stage performance resulted from activation of the endwall boundary layers, and suggested that further improvement might be expected by combination of end-bend stator blades and a highly loaded axial compressor stage could be developed by use of the CEF rotor.

UR - http://www.scopus.com/inward/record.url?scp=84973596665&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84973596665&partnerID=8YFLogxK

U2 - 10.1115/97-GT-248

DO - 10.1115/97-GT-248

M3 - Conference contribution

AN - SCOPUS:84973596665

T3 - Proceedings of the ASME Turbo Expo

BT - Aircraft Engine; Marine; Turbomachinery; Microturbines and Small Turbomachinery

PB - American Society of Mechanical Engineers (ASME)

ER -