Galdemir C. Botura

Development and Demonstration of Low Power Electrothermal De-icing System

Low Power Electrothermal De-icing (LPED) provides the potential for an improvement in ice protection performance, reliability, and a reduction in the bleed air energy extracted from the engine during icing flight conditions. The novel Low Power Electro De-icing system was developed to reduce the need for high energy levels as is required for conventional electro thermal ice protection systems. A low thermal mass and low energy system, with an average power density of less than 1.5 W/in 2 at -4 degrees Fahrenheit, was developed and manufactured compatible with the wear and erosion expectations of typical airfoil surfaces. The Low Power Electro Thermal De-icing system was successfully developed and tested in the Goodrich Icing Wind Tunnel (IWT), in flight behind an icing tanker and in flight in natural icing conditions on a technology demonstrator airplane during the 2003/2004 winter season. Test results have demonstrated the capability of the system to remove ice with minimal runback ice accumulation. The paper covers the Low Power Electro Thermal De-icing concept, development, test results from the Goodrich Icing Wind Tunnel (IWT), and test results from a technology demonstrator aircraft in flight behind an icing tanker and in natural icing conditions. Nomenclature

Concept Development of Low Power Electrothermal De-icing System

Aircraft icing is a science that requires innovation and understanding of icing formation. Today, airplane manufacturers are looking for alternatives way for removing ice of aircraft surfaces. Conventional electrothermal systems and long used bleed air systems demand considerable amount of energy from the generator and engine respectively. This can compromise airplane performance and energy availability for other subsystems. The novel Low Power Electrothermal De-icing System (LPED) was developed to address the concern of high energy required for an electrothermal ice protection system. The Low Power Electrothermal Deicing system was designed and tested to use an average power of less than 1.5 W/in 2 at -4 degrees Fahrenheit and still comply with the wear and erosion expectations of airfoil surfaces The Low Power Electrothermal De-icing System was successfully tested at the Goodrich Icing Wind Tunnel (IWT), in flight behind an icing tanker and in natural icing on a technology demonstrator airplane during the winter of 2003/2004. Test results have demonstrated the capability of the system to remove ice with little or no runback ice accumulation. This papers briefly describes the Low Power Electrothermal De-icing concept presented in the report AIAA-2005-1460 (reference 1), and discusses the endurance tests, hail tests and additional icing tunnel development tests performed during 2004 and 2005.

Develpment and Test Results on a High Efficientily Ice Protection System

Goodrich Aerostructures Group, Goodrich Materials and Simulation Center, and Goodrich Deicing and Specialty Systems Division are jointly developing a Highly Efficient Ice Protection System (HEIPS) for aircraft engine inlets. Engine Inlets designed with HEIPS technology, will improve efficiency of the engine and provide a lower weight inlet structure, when compared to a conventional Hot Air Thermal Anti-ice system. Eliminating the pressures and temperatures associated with the traditional pneumatic anti-ice system, allows for new nacelle concepts to be considered, including the use of conventional acoustic treatment in the lip area. The latter is important because aircraft noise is a major driver in current and future aircraft design, since international noise regulations are becoming more and more stringent.