Prediction of Ice Shape for Three-Dimensional Engine Inlet Based on the Proper Orthogonal Decomposition Method

Article Preview

Abstract:

To increase the prediction speed of ice accretion on the 3D engine inlet, the Proper Orthogonal Decomposition (POD) method was introduced. Taking the ice shapes from CFD numerical calculation results as samples, in view of the change of icing temperature, the procedures of predicting the ice shapes by POD method were introduced, which used ice shapes’ coordinates and ice accretion height as compute parameters, respectively. The POD and CFD ice shapes were found coincident, which indicates that the POD method can fast and accurately calculate the 3D engine inlet ice shapes. The results from the two different POD parameters were shown and compared, and the ice shapes were nearly the same, which means they have the same effect. However, the POD method based on ice accretion height is simpler and more appropriate

You might also be interested in these eBooks

Info:

Periodical:

Advanced Materials Research (Volumes 1008-1009)

Pages:

1011-1015

Citation:

Online since:

August 2014

Export:

Price:

Permissions CCC:

Permissions PLS:

Сopyright:

© 2014 Trans Tech Publications Ltd. All Rights Reserved

Share:

Citation:

* - Corresponding Author

[1] K.M. Al-Khalil, T.G. Keith and K.J. DeWitt: Icing Calculations on a Typical Commercial Jet Engine Inlet Nacelle. Journal of Aircraft, Vol. 34 (1997), p.87–93.

DOI: 10.2514/2.2139

Google Scholar

[2] C.S. Bidwell and M.G. Potapczuk. Users Manual for the NASA Lewis Three-Dimensional Ice Accretion Code (LEWICE3D). NASA TM-105974 (1993).

Google Scholar

[3] R.W. Gent: TRAJICE2 - A Combined Water Droplet Trajectory and Ice Accretion Prediction Program for Aerofoils. Royal Aerospace Establishment, Technical Report 90054 (1990).

Google Scholar

[4] T. Hedde and D. Guffond: ONERA Three-Dimensional Icing Model. AIAA Journal, Vol. 33(1995), pp.1038-1045.

DOI: 10.2514/3.12795

Google Scholar

[5] H. Beaugendre, F. Morency and W.G. Habashi: ICE3D, FENSAP-ICE'S 3D in-flight ice accretion module. AIAA 2002-0385 (2002).

DOI: 10.2514/6.2002-385

Google Scholar

[6] H.Q. Qu, S.W. Liu, L.P. Pang, T. Hu: Identifiability and Identification of Trace Continuous Pollutant Source. The ScientificWorld Journal, Volume 2014, Article ID 215104, 9 pages.

Google Scholar

[7] X.B. Shen, G.P. Lin, X.Q. Bu: Three-Dimensional Numerical Simulation of Ice Accretion at the Engine Inlet. Journal of Aircraft, Vol. 50 (2013), pp.635-642.

DOI: 10.2514/1.c031992

Google Scholar

[8] E. Ogretim: Aircraft ice accretion prediction based on neural networks. Journal of Aircraft, Vol. 43 (1996), pp.233-240.

DOI: 10.2514/1.16241

Google Scholar

[9] K. Nakakita and W.G. Habashi: Toward Real-Time Aero-Icing Simulation of Complete Aircraft via FENSAP-ICE. Journal of Aircraft, Vol. 47 (2010), pp.96-109.

DOI: 10.2514/1.44077

Google Scholar

[10] W. Cazemier, R. W. Verstappen: Proper Orthogonal Decomposition and Low-Dimensional Models for Driven Cavity. Physics of Fluids, Vol. 10 (1998), p.1685–1699.

DOI: 10.1063/1.869686

Google Scholar

[11] P. Ding, W.Q. Tao: Reduced Order Modeling with the Proper Orthogonal Decomposition. Journal of Engineering Thermo physics, Vol. 30 (2009), pp.1019-1021.

Google Scholar

[12] Z. Ostrowski, R.A. Białecki: Estimation of constant thermal conductivity by use of Proper Orthogonal Decomposition. Comput Mech, Vol. 37 (2005), pp.52-59.

DOI: 10.1007/s00466-005-0697-y

Google Scholar

[13] X.B. Shen, G.P. Lin, S.H. Yang: Analysis on three dimensional water droplets impingement characteristics of engine inlet. Journal of Beijing University of Aeronautics and Astronautics, Vol. 31 (2011) pp.1-5.

Google Scholar