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Research Papers

Low Order Modeling for Fan and Outlet Guide Vanes in Aero-Engines

[+] Author and Article Information
Jiahuan Cui

Department of Engineering,
University of Cambridge,
Cambridge, CB2 1PZ, UK
e-mail: jiahuancui@intl.zju.edu.cn

Rob Watson

Department of Engineering,
University of Cambridge,
Cambridge, CB2 1PZ, UK
e-mail: R.Watson@qub.ac.uk

Yunfei Ma

Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
e-mail: ym324@cam.ac.uk

Paul Tucker

Department of Engineering,
University of Cambridge,
Cambridge CB2 1PZ, UK
e-mail: pgt23@cam.ac.uk

1Present address: ZJUI institute, Zhejiang University, Haining 314400, China; School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310007, China.

2Present address: School of Mechanical and Aerospace Engineering, Queen's University Belfast, Belfast BT7 1NN, Northern Ireland, UK.

3Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 1, 2018; final manuscript received December 3, 2018; published online January 16, 2019. Editor: Kenneth Hall.

J. Turbomach 141(3), 031002 (Jan 16, 2019) (9 pages) Paper No: TURBO-18-1143; doi: 10.1115/1.4042202 History: Received July 01, 2018; Revised December 03, 2018

Intakes of reduced length have been proposed with the aim of producing aero-engines with higher efficiency and reduced weight. As the intake length decreases, it is expected that stronger effects of the fan on the flow over the intake lip will be seen. If the effects of the fan cannot be ignored, a low-cost but still accurate fan model is of great importance for designing a short-intake. In this paper, a low order rotor/stator model, the immersed boundary method with smeared geometry (IBMSG), has been further developed and validated on a rig test case. The improved IBMSG is more robust than the original. The rig test case used for validation features a low-pressure compression system with a nonaxisymmetric inflow, which is representative of the inlet condition of an aero-engine at its cruise condition. Both the fan and the outlet guide vanes (OGVs) are modeled using IBMSG. A detailed analysis is carried out on the flow both upstream and downstream of the fan. After validating the IBMSG method against the rig test case, a short-intake case, coupled with a fan designed for the next generation of aero-engines, is further investigated. It is found that compared with the intake-alone case, the inflow distortion at the fan face is significantly reduced by the presence of fan. Due to this increased interaction between the fan and the flow over the intake lip, accounting for the effects of the downstream fan is shown to be essential when designing a short intake.

Copyright © 2019 by ASME
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References

MacIsaac, B. , and Langton, R. , 2011, Gas Turbine Propulsion Systems, Wiley, Hoboken, NJ.
Cao, T. , Vadlamani, N. R. , Tucker, P. G. , Smith, A. R. , Slaby, M. , and Sheaf, C. T. J. , 2017, “ Fan–Intake Interaction Under High Incidence,” ASME J. Eng. Gas Turbines Power, 139(4), p. 41204. [CrossRef]
Peters, A. , Spakovszky, Z. S. , Lord, W. K. , and Rose, B. , 2014, “ Ultrashort Nacelles for Low Fan Pressure Ratio Propulsors,” ASME J. Turbomach., 137(2), p. 021001. [CrossRef]
Joo, W. G. , and Hynes, T. P. , 1997, “ The Simulation of Turbomachinery Blade Rows in Asymmetric Flow Using Actuator Disks,” ASME J. Turbomach., 119(4), pp. 723–732. [CrossRef]
Kaji, S. , and Okazaki, T. , 1970, “ Propagation of Sound Waves Through a Blade Row—Part I: Analysis Based on the Semi-Actuator Disk Theory,” J. Sound Vib., 11(3), pp. 339–353. [CrossRef]
Gong, Y. , 1999, “ A Computational Model for Rotating Stall and Inlet Distortions in Multistage Compressors,” Ph.D. thesis, Massachusetts Institute of Technology, Cambridge, MA. http://hdl.handle.net/1721.1/9733
Cao, T. , Hield, P. , and Tucker, P. G. , 2017, “ Hierarchical Immersed Boundary Method With Smeared Geometry,” J. Propul. Power, 33(5), pp 1151–1163.
Fadlun, E. , Verzicco, R. , Orlandi, P. , and Mohd-Yusof, J. , 2000, “ Combined Immersed-Boundary Finite Difference Methods for Three-Dimensional Complex Flow Simulations,” J. Comput. Phys., 161(1), pp. 35–60. [CrossRef]
Watson, R. , Cui, J. , Ma, Y. , Tyacke, J. , Vadlamani, N. , Alam, M. , Dai, Y. , Tucker, P. , Cao, T. , Hield, P. , Wilson, M. , Menzies, K. , and Sheaf, C. , 2017, “ Improved Hierarchical Modelling for Aerodynamically Coupled Systems,” ASME Paper No. GT2017-65223.
Simon, J. F. , and Leonard, O. , 2007, “ Modeling of 3D Losses and Deviations in a Throughflow Analysis Tool,” J. Therm. Sci., 16(3), pp. 208–214. [CrossRef]
Watson, R. , 2013, “ Large Eddy Simulation of Cutback Trailing Edges for Film Colling Turbine Blades,” Ph.D. thesis, University of Cambridge, Cambridge, UK.
Cui, J. , and Tucker, P. , 2017, “ Numerical Study of Purge and Secondary Flows in a Low-Pressure Turbine,” ASME J. Turbomach., 139(2), p. 021007.
Fidalgo, V. J. , Hall, C. A. , and Colin, Y. , 2012, “ A Study of Fan-Distortion Interaction Within the NASA Rotor 67 Transonic Stage,” ASME J. Turbomach., 134(5), pp. 51011–51012. [CrossRef]
Liu, Y. , Yu, X. , and Liu, B. , 2008, “ Turbulence Models Assessment for Large-Scale Tip Vortices in an Axial Compressor Rotor,” J. Propul. Power, 24(1), pp. 15–25. [CrossRef]
Liu, Y. , Lu, L. , Fang, L. , and Gao, F. , 2011, “ Modification of Spalart–Allmaras Model With Consideration of Turbulence Energy Backscatter Using Velocity Helicity,” Phys. Lett. A, 375(24), pp. 2377–2381. [CrossRef]

Figures

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Fig. 1

Sketch of the shock induced separation over a short-intake lip

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Fig. 2

Diagram for vn and un

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Fig. 3

Blade geometric blockage

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Fig. 4

Sketch of the computational domain of the rig geometry and the locations where experimental data are available

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Fig. 5

Main components in the computational configuration (surfaces are colored by radius)

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Fig. 6

Comparison of operating point between numerical results and experiments: specific mass flow = m˙Ttot/Ptot

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Fig. 7

Static pressure at fan face (looking from upstream)

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Fig. 8

Interstage quantities

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Fig. 9

Total pressure variation in the circumferential direction at OGV leading edge at 30%, 60%, and 80% blade heights: measurements, ; URANS, ; IBMSG,. (Colored figure can be found online) The reference location (0deg) can be found in Fig. 10.

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Fig. 10

Static pressure (from URANS) between the fan and OGV with pylons at the background

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Fig. 11

Comparison of the whirl angle at the OGV leading edge: (a) URANS and (b) IBMSG

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Fig. 12

Comparison of the Mach number at the OGV leading edge: (a) URANS and (b) IBMSG

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Fig. 13

Unwrapped view of the Mach number at 30% of OGV span for (a) IBMSG and (b) URANS

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Fig. 14

Unwrapped view of the Mach number at 60% of OGV span for (a) IBMSG and (b) URANS

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Fig. 15

Unwrapped view of the Mach number at 80% of OGV span for (a) IBMSG and (b) URANS

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Fig. 16

The computational domain and blocking topology for the short-intake case at the plane of symmetry of the intake

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Fig. 17

Flow solution at the angle of attack = 23 deg: (a) Mach number on the plane of symmetry of the intake and (b) total pressure at the fan face

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Fig. 18

Flow solution at a larger angle of attack: (a) Mach number on the plane of symmetry of the intake and (b) total pressure at the fan face

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Fig. 19

DC60 variation at different angles of attack. The intake-alone calculation is also superimposed for comparison.

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Fig. 20

Shock position: (a) static pressure along the bottom intake lip and (b) shock position at different angles of attack

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