Development of body force model for steady inlet distortions in high-speed multistage compressor

Abstract

This study aims at establishing a three-dimensional numerical model, compressor aerodynamic performance analysis model, to simulate the impact of complicated distorted flow on multistage axial flow compressor based on the body force model. The model solves the compressible three-dimensional Euler equations, which are modified to include source terms representing the effect of the blade rows. In this study, the association between blade source terms and entry Mach number together with attack angle could be established with the deviation angle model and loss model. In this paper, compressor aerodynamic performance analysis model is used to evaluate the effect of inlet circumferential total pressure distortion and swirl distortion on a five-stage high-pressure compressor. Calculated operating maps for compressor agree well with the experimental results. Meanwhile, the traveling process of inlet distortions in the multistage compressor is correctly revealed. The wide application prospect of the model can be seen in the area of inlet distortion problems.

Keywords

Multistage compressor body force inlet distortions source term numerical simulation

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References

Mazzawy

. Multiple segment parallel compressor model for circumferential flow distortion. ASME J Eng Power 1997; 99: 288–296.

Hawthorne

. Non-axisymmertic flow through annular actuator disks: Inlet distortion problems. ASME J Eng Power 1978; 100: 604–617.

Dunham

. Non-axisymmetric flows in axial flow compressors. Institution of Mechanical Engineers Monograph 1965, pp. 1–32.

Fidalgo

Hall

Colin

. A study of fan-distortion interaction within the NASA Rotor 67 transonic stage. J Turbomach 2012; 134: 051011–051011.

Lesser A, Iseler J and Niehuis R. Numerical investigation of a highly loaded axial compressor stage with inlet distortions. ASME paper GT2011-46457, 2011.

Yao J, Gorrell SE and Wadia AR. A time-accurate CFD analysis of inlet distortion induced swirl in multistage fans. AIAA paper, 2007-5059, 2007.

Hale AA, Davis MW Jr and Kneile KR. Turbine engine analysis compressor code: TEACC—Part I: Technical approach and steady results. AIAA-94-0418, 1994.

Hale A, Chalk J, Klepper J, et al. Turbine engine analysis compressor code: TEACC — Part II: Multi-stage compressors and inlet distortion. AIAA-99-3214, 1999.

Hale

O'Brien

. A three-dimensional turbine engine analysis compressor code (TEACC) for steady-state inlet distortion. J Turbomach 1998; 120: 422–430.

10.

Hale A, Davis M and Sirbaugh J. A numerical simulation capability for analysis of aircraft inlet–engine compatibility. ASME paper GT-2004-53473, 2004.

11.

Gong YF, Tan CS, Gordon KA, et al. A computational model for short wavelength stall inception and development in multistage compressors. ASME paper 98-GT-476, 1998.

12.

Gong

. A computational model for rotating stall and inlet distortions in multistage compressors, Cambridge: Massachusetts Institute of Technology, 1998.

13.

Chima RV. A three-dimensional unsteady CFD model of compressor stability. ASME paper, GT-2006-90040.

14.

Marble

. Three-dimensional flow in turbomachines, aerodynamics of turbines and compressors, Princeton: Princeton University Press, 1964.

15.

Johnsen IA and Bullock RO. Aerodynamic design of axial-flow compressors. NASA, SP-36, 1965.

16.

Wright PI and Miller DC. An improved compressor performance prediction model. In: Conference on turbomachinery, London, UK, 1991, pp.69–82.

17.

Liou

. A sequel to AUSM, Part II: AUSM⁺-up for all speeds. J Comput Phys 2006; 214: 137–170.

18.

Koch

. Stalling pressure rise capability of axial flow compressor stages. ASME J Eng Power 1981; 103: 645–656.

19.

Jahnen W. Untersuchung von Strömungs-Instabilitaeten in Einem Mehrstufigen Axialverdichter unter den Einfluss von Eintrittsstoerungen. Doctor Dissertation, Universitaet der Bundeswehr Muenchen, Germany, 1998.