Numerical Simulation of Steady Air Injection Flow Control Effects on a Transonic Axial Flow Compressor

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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%.

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Periodical:

Edited by:

Jing Guo

Pages:

352-357

Citation:

I. Benhegouga and C. Yang, "Numerical Simulation of Steady Air Injection Flow Control Effects on a Transonic Axial Flow Compressor", Applied Mechanics and Materials, Vol. 224, pp. 352-357, 2012

Online since:

November 2012

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[1] M.W. Müler, H.P. Schiffer, and C. Hah, in: Effect of circumferential grooves on the aerodynamic performance of an axial single stage transonic compressor . ASME paper, GT2007-27365, (2007).

DOI: https://doi.org/10.1115/gt2007-27365

[2] I. Wilke, H.P. Kau, in: A numerical investigation of the influence of casing treatments on the tip leakage flow in an hpc front stage. ASME paper, GT2002-30642, (2002).

DOI: https://doi.org/10.1115/gt2002-30642

[3] S. Aamir, J.A. John, in: Flow mechanism for stall margin improvement due to circumferential casing grooves on axial compressors. ASME journal of turbomachine, vol (127), 708-717, (2005).

DOI: https://doi.org/10.1115/1.2008970

[4] B. Jinwoo, S.B. Kenneth, and S.T. Choon, in: Active control of tip clearance flow in axial compressors. ASME paper, GT2003-38661, (2003).

DOI: https://doi.org/10.1115/gt2003-38661

[5] H.B. Behnam, G. Kaveh, F. Bijan, A.T. Joao, and C.I. Paul, in: A new design for tip injection in transonic axial compressors. ASME paper, GT2006-90007, (2006).

DOI: https://doi.org/10.1115/gt2006-90007

[6] S. Chunhua, R. Michael, in: Numerical simulations of rotor 35 with and without tip injection using an arbitrary mach number flow solver. AIAA aerospace sciences meeting and exhibit, Reno, Nevada, (2004).

DOI: https://doi.org/10.2514/6.2004-372

[7] H. Khaleghi, J.A. Teixeira, A.M. Tousi, and M. Boroomand, in: Parametric study of injection angle effects on stability of transonic axial compressors. Propulsion and power, 24(5), 1100-1107, (2004).

DOI: https://doi.org/10.2514/1.34817

[8] K.L. Suder, M.D. Hathaway, A.T. Scott, J.S. Anthony, and B.B. Michelle, in: Compressor stability enhancement using discrete tip injection. ASME journal of turbomachine, vol (123), 14-23, (2001).

DOI: https://doi.org/10.1115/1.1330272

[9] C.M. Robert, E. Katherine, A.B. Grover, and S. Seyed, in: Control of tip-clearance flow in a low Speed axial compressor rotor with plasma actuation. ASME journal of turbomachinery, vol 134, (2011).

DOI: https://doi.org/10.1115/1.4003083

[10] I. Masahiro, S. Taufan, U. Hironobu, and S. Daisaku, in: Suppression of unstable flow at small flow rates in a centrifugal blower by controlling tip leakage flow and reverse flow. ASME paper, GT2004-53400, (2004).

DOI: https://doi.org/10.1115/gt2004-53400

[11] I. Masahiro, D. Sakaguchi, and H. Ueki, in: Effect of pre-whirl on unstable flow suppression in a centrifugal impeller with ring groove arrangement. ASME paper, GT2006-90400, (2006).

DOI: https://doi.org/10.1115/gt2006-90400

[12] ASME Turbomachinery Committee, CFD Code Assessment in Turbomachinery – Data Report, (1994).

[13] D.M. Royce, R. Lonnie, in: Performance of Single-Stage Axial-Flow Transonic Compressor with Rotor and Stator Aspect Ratios of 1. 19 and 1. 26, Respectively, and with Design Pressure Ratio of 2. 05. NASA Technical Paper 1659, (1980).