Development of an Engine Anti-ice Protection System using Experimental and Numerical Approaches
Document Number: 2007-01-3355
Date Published: September 2007
Author(s):
Rodgrigo Hoffman Domingos - EMBRAER
Marcelo Pustelnik - EMBRAER
Luis Gustavo Trapp - EMBRAER
Guilherme A L Da Silva - EMBRAER
William Campo - EMBRAER
Luis C. Santos - EMBRAER
Abstract:
This paper describes part of the process of development of engine inlet anti-ice system, based on numerical simulation and icing wind tunnel tests. A number of critical cases are selected spanning the Appendix C. At these selected points, a set of tools for thermal analysis is applied and different piccolo tubes designs are analyzed. The selected configurations and conditions are tested in an Icing Wind Tunnel, where the piccolo flow parameters are optimized and data is collected to establish a basis for validation of the numerical tools. Using the experimental data, a high fidelity set of thermal analysis tools is validated, which can be used to explore the whole design space of system in order to refine the design for a second iteration (if necessary). The comparison of numerical and experimental data has shown the validity and accuracy of the procedure.
File Size: 464K
Product Status: In Stock
See other papers presented at 2007 SAE Aircraft and Engine Icing International Conference, September 2007, Seville, SPAIN, Session: In-flight Ice Protection System Modeling
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