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Integrated Engine Inlet Thermal Anti-Icing and Environmental Control System (TAI/ECS)
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English
Abstract
The integrated engine inlet thermal anti-icing and environmental control system (TAI/ECS) for subsonic transport airplanes was conceived primarily for the efficient use of available energy and minimum engine bleed air extraction. The concept employs the engine inlet leading edge as the heat exchanger to provide ice protection for the engine inlet surfaces and to cool bleed air for the environmental control system. The results of a study conducted for a typical wide-body airplane using high bypass ratio engines show that the system concept will result in potential improvements in airplane operation and engine maintenance.
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Citation
Shah, A., "Integrated Engine Inlet Thermal Anti-Icing and Environmental Control System (TAI/ECS)," SAE Technical Paper 760517, 1976, https://doi.org/10.4271/760517.Also In
References
- Greenly K. H. “Recent Developments in Aircraft Ice Protection.” Aircraft Engineering 35 4 1963
- “Fuel Conservation.” Boeing Airliner January 1974
- “Fuel Conservation Possibilities for Terminal Area Compatible Aircraft.” Boeing Commercial Airplane Company May 1975
- Shah A. D. “Heat Transfer in a Double-Skin Heat Exchanger With Flow Through Rectangular Passages.” Boeing document D6-43267 June 23 1975