This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Passive Aircraft Anti Icing System Using Waste Heat
Annotation ability available
Sector:
Language:
English
Abstract
A passive anti icing system for the engine cowl of the Global Hawk UAV was designed and evaluated under a NASA Phase I SBIR Program. The system utilizes five Loop Heat Pipes to remove 3.8 kW of waste heat from the hydraulic system and deliver it to the engine inlet during icing conditions. During non-icing conditions the heat is bypassed to relief valves on the fuel ullage tank to maintain their temperature above freezing. The system masses 18.5 kg and replaces some 15 lbs of existing equipment. A Phase II program to integrate the system aboard the aircraft is underway with the goal of starting flight tests in early 1999.
Recommended Content
Technical Paper | Loop Heat Pipe Technology for Aircraft Anti-Icing Applications |
Aerospace Standard | Weather |
Technical Paper | Development of a Unique Icing Spray System for a New Facility for Certification of Large Turbofan Engines |
Citation
Phillips, A. and Gernert, N., "Passive Aircraft Anti Icing System Using Waste Heat," SAE Technical Paper 981542, 1998, https://doi.org/10.4271/981542.Also In
References
- Anderson William Hoff Sandra Winstanley David Phillips John DelPorte Scott “Heat Pipe Cooling of Turboshaft Engines” 38 th International Gas Turbine and Aeroengine Congress and Exposition Cincinnati, Ohio May 24-27 1993
- Anderson W. G. Chow P. Yerkes K. “Loop Heat Pipes for Anti Icing of Gas Turbine Inlets” Ninth International Heat Pipe Conference Albuquerque, NM May 1-5 1995
- Gernert N.J. Baldassarre G.J. Gottschlich J.M. “Loop Heat Pipes for Avionics Thermal Control” Aerospace Atlantic Conference 1996 SAE# 961318
- Phillips A.L. Fale J.E. Gernert N.J. Sarraf D.B. Bienert W.J. “Loop Heat Pipe Qualification for High Vibration and High-G Environments” 36th AIAA Aerospace Sciences Meeting and Exhibit Reno NV Jan. 12-15 1998