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2013 (Vol. 5, Issue: 04)
Article Information:

Steady Air Injection Flow Control Parameters in a Transonic Axial Compressor

Islem Benhegouga and Yang Ce
Corresponding Author:  Islem Benhegouga 

Key words:  Air injection, numerical simulation, transonic axial compressor, , , ,
Vol. 5 , (04): 1441-1448
Submitted Accepted Published
July 21, 2012 August 21, 2012 February 01, 2013

In the present study, steady air injection upstream of the tip blade leading edge was studied. To reveal the mechanism, steady numerical simulations were performed on a transonic axial compressor, NASA rotor 37. The injection angle α is 20 and three injector axial position were studied, respectively 9, 18 and 27% upstream of the axial chord length at blade tip (ca). For each position a different injection mass flow rate and different injection yaw angles were simulated. The results show at design speed (n =17188 r/min), with injector position at 9% ca, injection mass flow rate of 2% and injection yaw angle between -20 and -30, the mass flow rate at stall can decrease for approximately 3%, but others compressor parameters were affected such as the total pressure ratio. With injector positioned at 27% ca, the decrease in the mass flow rate at stall is less obvious, but the effect on the compressor pressure ratio is benefic.
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  Cite this Reference:
Islem Benhegouga and Yang Ce, 2013. Steady Air Injection Flow Control Parameters in a Transonic Axial Compressor.  Research Journal of Applied Sciences, Engineering and Technology, 5(04): 1441-1448.
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ISSN (Online):  2040-7467
ISSN (Print):   2040-7459
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