This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Engine Icing Modeling and Simulation (Part I): Ice Crystal Accretion on Compression System Components and Modeling its Effects on Engine Performance
Technical Paper
2011-38-0025
ISSN: 0148-7191, e-ISSN: 2688-3627
Annotation ability available
Sector:
Language:
English
Abstract
During the past two decades the occurrence of ice accretion within commercial high bypass aircraft turbine engines under certain operating conditions has been reported. Numerous engine anomalies have taken place at high altitudes that were attributed to ice crystal ingestion such as degraded engine performance, engine roll back, compressor surge and stall, and even flameout of the combustor. As ice crystals are ingested into the engine and low pressure compression system, the air temperature increases and a portion of the ice melts allowing the ice-water mixture to stick to the metal surfaces of the engine core. The focus of this paper is on estimating the effects of ice accretion on the low pressure compressor, and quantifying its effects on the engine system throughout a notional flight trajectory. In this paper it was necessary to initially assume a temperature range in which engine icing would occur. This provided a mechanism to locate potential component icing sites and allow the computational tools to add blockages due to ice accretion in a parametric fashion. Ultimately the location and level of blockage due to icing would be provided by an ice accretion code. To proceed, an engine system modeling code and a mean line compressor flow analysis code were utilized to calculate the flow conditions in the fan-core and low pressure compressor and to identify potential locations within the compressor where ice may accrete. Note that there is a baseline value of aerodynamic blockage due to low velocity air near the compressor inner and outer walls and blade surfaces (boundary layer blockage). There is also a blockage due to the blade metal thickness. In this study, the “additional blockage” refers to blockage due to the accretion of ice on the metal surfaces. Once the potential locations of ice accretion are identified, the levels of additional blockage due to accretion were parametrically varied to estimate the effects on the low pressure compressor blade row performance operating within the engine system environment. This study includes detailed analysis of compressor and engine performance during cruise and descent operating conditions at several altitudes within the notional flight trajectory. The purpose of this effort is to develop the codes to provide a predictive capability to forecast the onset of engine icing events, such that they could help in the avoidance of these events.
It has been reported that ice crystal accretion in gas turbine engines is dependent on the amount of mixed phase conditions (liquid and solid) that exist. In addition, the problem of ice accretion is highly multi-disciplinary, since it involves heat transfer from the air to the compressor metal surfaces. The first phase of this study focuses on addressing the thermodynamic cycle through the engine system code and the mean line flow analysis through the compressor through a flight trajectory. The second phase of this study focuses on the ice particle physics in the flow field that was computed in the first phase.
Recommended Content
Technical Paper | Two-Way Flow Coupling in Ice Crystal Icing Simulation |
Technical Paper | FENSAP-ICE: 3D Simulation, and Validation, of De-icing with Inter-cycle Ice Accretion |
Technical Paper | Flow Field Predictions of the NASA Glenn Icing Research Tunnel |
Authors
Citation
Jorgenson, P., Veres, J., Wright, W., and May, R., "Engine Icing Modeling and Simulation (Part I): Ice Crystal Accretion on Compression System Components and Modeling its Effects on Engine Performance," SAE Technical Paper 2011-38-0025, 2011, https://doi.org/10.4271/2011-38-0025.Also In
References
- Mason, J.G. Strapp, J.W. Chow, P. “The Ice Particle Threat to Engines in Flight,” AIAA-2006-206-739
- Mason, J.G. Chow, P. Fuleki, D.M. “Understanding Ice Crystal Accretion and Shedding Phenomenon in Jet Engines Using a Rig Test,” GT2010-22550
- Jones, S.M. “An Introduction to Thermodynamic Performance Analysis of Aircraft Gas Turbine Engine Cycles Using the Numerical Propulsion System Simulation Code,” NASA/TM-2007-214690
- Veres, J.P. “Axial and Centrifugal Compressor Mean Line Flow Analysis Method,” AIAA-2009-1641, NASA/TM-2009-215585
- Veres, J.P. Thurman, D. “Conceptual Design of Compressor for Two Spool LCTR-2 Engine” NASA/TM-2011-216264
- Struk, P. Currie, T. Wright, W. Knezevici, D. et al. “Fundamental Ice Crystal Accretion Physics Studies,” SAE Technical Paper 2011-38-0018 2011 10.4271/2011-38-0018
- Wright, William B. Jorgenson, Philip C. E. Veres, Joseph P. “Mixed Phase Modeling in GlennICE with Application to Engine Icing,” AIAA-2010-81093
- McCullers, L.A. “Aircraft Configuration Optimization Including Optimized Flight Profiles,” Proceedings of the Symposium on Recent Experiences in Multidisciplinary Analysis and Optimization, NASA CP 2327 April 1984
- Veres, Joseph P. Jorgenson, Philip C. E. Wright, William B. “Modeling of Engine Icing and its Effects on Compression and Engine System Performance,” NASA/TM-2011-217034
- Wright, W.B. Potapczuk, M.G. Levinson, L.H. “Comparison of LEWICE and GlennICE in the SLD Regime” AIAA-2008-0439
- Crowe, C. Sommerfeld, M. Tsuji, Y. Multiphase Flows with Droplets and Particles CRC Press 1998
- Higa, M. Arakawa, M. Maeno, N. “Measurements of Restitution Coefficients of Ice at Low Temperatures” Planet. Space Sci 44 9 917 925 1996
- Al-Khalil, K. “Assessment of Effects of Mixed Phase Icing Conditions on Thermal Protection Systems” DOT/FAA/AR-03/48 May 2003