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A Computational Investigation of Icing effects on an S-Duct Inlet
Jin, Wonjin Taghavi, Ray R. Farokhi, Saeed
Jin, Wonjin
Taghavi, Ray R.
Farokhi, Saeed
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Abstract
The effects of a typical glaze ice accretion shape on the performance of the M2129 S-duct inlet are computationally
investigated for a range of flight Mach numbers. A Reynolds-Averaged Navier-Stokes (RANS) code with k-o> turbulence
model is used to simulate the compressible viscous flow in the S-duct inlet. The glaze ice accretion on the cowl lip is
modeled on a steady-state basis from NASA LEWICE3D code. The results show that the total pressure recovery is reduced
and the compressor face distortion level is increased with flight Mach number. A reduction of 22.8% in total pressure
recovery is calculated for a flight Mach number of 0.85 in fully-developed glazed ice condition. The massive flow
separations in the inlet induced by the glaze ice horn shapes also create a mass flow reduction in the inlet between 27 and
33% as compared to clean inlet for flight Mach numbers of 0.13 and 0.475, respectively. The combined effects of reduced
total pressure recovery and the reduced mass flow rate results in a reduction of engine thrust between ~30 and 60% from low
speed flight to Mach 0.85.
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This is the published version. Copyright 2010 © Freund Publishing House Ltd.
Date
2010-12
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Freund Publishing House
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Jin, Wonjin, Ray R. Taghavi, and Saeed Farokhi. "A Computational Investigation of Icing Effects on an S-Duct Inlet." International Journal of Turbo and Jet Engines 27.3-4 (2010). http://dx.doi.org/10.1515/TJJ.2010.27.3-4.277