Numerical simulation of steady air injection flow control effects on a transonic axial flow compressor

Islem Benhegouga; Ce Yang

doi:10.4028/www.scientific.net/AMM.224.352

Numerical simulation of steady air injection flow control effects on a transonic axial flow compressor

Islem Benhegouga^*, Ce Yang

^*Corresponding author for this work

School of Mechanical Engineering

Beijing Institute of Technology

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › peer-review

1 Citation (Scopus)

Abstract

In this work, steady air injection upstream of the blade leading edge was used in a transonic axial flow compressor, NASA rotor 37. The injectors were placed at 27 % upstream of the axial chord length at blade tip, the injection mass flow rate is 3% of the chock mass flow rate, and 3 yaw angles were used, respectively -20°, -30°, and -40°. Negative yaw angles were measured relative to the compressor face in opposite direction of rotational speeds. To reveal the mechanism, steady numerical simulations were performed using FINE/TURBO software package. The results show that the stall mass flow can be decreased about 2.5 %, and an increase in the total pressure ratio up to 0.5%.

Original language	English
Title of host publication	Industrial Design and Mechanical Power
Pages	352-357
Number of pages	6
DOIs	https://doi.org/10.4028/www.scientific.net/AMM.224.352
Publication status	Published - 2012
Event	2012 International Conference on Industrial Design and Mechanical Power, ICIDMP 2012 - Huangshan, China Duration: 10 Jul 2012 → 11 Jul 2012

Publication series

Name	Applied Mechanics and Materials
Volume	224
ISSN (Print)	1660-9336
ISSN (Electronic)	1662-7482

Conference

Conference	2012 International Conference on Industrial Design and Mechanical Power, ICIDMP 2012
Country/Territory	China
City	Huangshan
Period	10/07/12 → 11/07/12

Keywords

Numerical simulation
Tip injection flow control
Transonic axial flow compressor

Access to Document

10.4028/www.scientific.net/AMM.224.352

Cite this

@inproceedings{33b55c35070047f4a2b5b80dfc58b930,

title = "Numerical simulation of steady air injection flow control effects on a transonic axial flow compressor",

abstract = "In this work, steady air injection upstream of the blade leading edge was used in a transonic axial flow compressor, NASA rotor 37. The injectors were placed at 27 % upstream of the axial chord length at blade tip, the injection mass flow rate is 3% of the chock mass flow rate, and 3 yaw angles were used, respectively -20°, -30°, and -40°. Negative yaw angles were measured relative to the compressor face in opposite direction of rotational speeds. To reveal the mechanism, steady numerical simulations were performed using FINE/TURBO software package. The results show that the stall mass flow can be decreased about 2.5 %, and an increase in the total pressure ratio up to 0.5%.",

keywords = "Numerical simulation, Tip injection flow control, Transonic axial flow compressor",

author = "Islem Benhegouga and Ce Yang",

year = "2012",

doi = "10.4028/www.scientific.net/AMM.224.352",

language = "English",

isbn = "9783037855058",

series = "Applied Mechanics and Materials",

pages = "352--357",

booktitle = "Industrial Design and Mechanical Power",

note = "2012 International Conference on Industrial Design and Mechanical Power, ICIDMP 2012 ; Conference date: 10-07-2012 Through 11-07-2012",

}

Benhegouga, I & Yang, C 2012, Numerical simulation of steady air injection flow control effects on a transonic axial flow compressor. in Industrial Design and Mechanical Power. Applied Mechanics and Materials, vol. 224, pp. 352-357, 2012 International Conference on Industrial Design and Mechanical Power, ICIDMP 2012, Huangshan, China, 10/07/12. https://doi.org/10.4028/www.scientific.net/AMM.224.352

TY - GEN

T1 - Numerical simulation of steady air injection flow control effects on a transonic axial flow compressor

AU - Benhegouga, Islem

AU - Yang, Ce

PY - 2012

Y1 - 2012

N2 - In this work, steady air injection upstream of the blade leading edge was used in a transonic axial flow compressor, NASA rotor 37. The injectors were placed at 27 % upstream of the axial chord length at blade tip, the injection mass flow rate is 3% of the chock mass flow rate, and 3 yaw angles were used, respectively -20°, -30°, and -40°. Negative yaw angles were measured relative to the compressor face in opposite direction of rotational speeds. To reveal the mechanism, steady numerical simulations were performed using FINE/TURBO software package. The results show that the stall mass flow can be decreased about 2.5 %, and an increase in the total pressure ratio up to 0.5%.

AB - In this work, steady air injection upstream of the blade leading edge was used in a transonic axial flow compressor, NASA rotor 37. The injectors were placed at 27 % upstream of the axial chord length at blade tip, the injection mass flow rate is 3% of the chock mass flow rate, and 3 yaw angles were used, respectively -20°, -30°, and -40°. Negative yaw angles were measured relative to the compressor face in opposite direction of rotational speeds. To reveal the mechanism, steady numerical simulations were performed using FINE/TURBO software package. The results show that the stall mass flow can be decreased about 2.5 %, and an increase in the total pressure ratio up to 0.5%.

KW - Numerical simulation

KW - Tip injection flow control

KW - Transonic axial flow compressor

UR - http://www.scopus.com/inward/record.url?scp=84870816079&partnerID=8YFLogxK

U2 - 10.4028/www.scientific.net/AMM.224.352

DO - 10.4028/www.scientific.net/AMM.224.352

M3 - Conference contribution

AN - SCOPUS:84870816079

SN - 9783037855058

T3 - Applied Mechanics and Materials

SP - 352

EP - 357

BT - Industrial Design and Mechanical Power

T2 - 2012 International Conference on Industrial Design and Mechanical Power, ICIDMP 2012

Y2 - 10 July 2012 through 11 July 2012

ER -

Numerical simulation of steady air injection flow control effects on a transonic axial flow compressor

Abstract

Publication series

Conference

Keywords

Access to Document

Other files and links

Fingerprint

Cite this