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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
Abstract:

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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