An embedded turbofan deicer system (ETDS) may eliminate the ingested ice crystal icing problem plaguing high bypass turbofan engines operating at high altitudes near convective tropical storms: icing occurring on the surfaces of the engine's rotating engine spinner, fan blades, low pressure compress
An embedded turbofan deicer system (ETDS) may eliminate the ingested ice crystal icing problem plaguing high bypass turbofan engines operating at high altitudes near convective tropical storms: icing occurring on the surfaces of the engine's rotating engine spinner, fan blades, low pressure compressor casing and low pressure compressor and causing loss of power and on occasion engine flameouts. The invention supplies electricity to heat these engine parts using at least one reversed permanent magnet electric generator (reversed PMEG) driven by the turbofan's central drive shaft with all parts of the ETDS mounted internal to the engine in presently unused internal spaces without requiring modifications to the existing engine. All electric power produced by the rotating reversed PMEG supplied directly to rotating engine parts requiring heat for deicing. A unique method to deice metal, composite and metal/composite fan blades is included in the invention using electricity from the reversed PMEG.
대표청구항▼
1. An air-breathing jet engine comprising: at least one rotatable shaft; anda deicing apparatus, comprising: a reversed permanent magnet electric generator (PMEG) driven by the at least one rotatable shaft, wherein the reversed PMEG has at least one fixed magnet and at least one rotatable winding;an
1. An air-breathing jet engine comprising: at least one rotatable shaft; anda deicing apparatus, comprising: a reversed permanent magnet electric generator (PMEG) driven by the at least one rotatable shaft, wherein the reversed PMEG has at least one fixed magnet and at least one rotatable winding;an electrical resistive thermal material positioned on at least a portion of the air-breathing jet engine;at least one electrical ground connection connected between the at least one rotatable winding and an aircraft airframe; andat least one electrical connection between the reversed PMEG and the electrical resistive thermal material. 2. The air-breathing jet engine of claim 1, wherein the reversed PMEG is positioned within an interior space in the nose-end of the air-breathing jet engine between the at least one rotatable shaft and a rotatable low pressure compressor casing of the air-breathing jet engine. 3. The air-breathing jet engine of claim 1, wherein the reversed PMEG further comprises a stator having the at least one fixed magnet, wherein the at least one rotatable winding is positioned exterior of the stator. 4. The air-breathing jet engine of claim 3, wherein the at least one rotatable winding is connected to the at least one rotatable shaft of the air-breathing jet engine. 5. The air-breathing jet engine of claim 3, wherein the at least one rotatable winding is connected to a rotatable low-pressure compressor casing of the air-breathing jet engine. 6. The air-breathing jet engine of claim 3, wherein the stator is affixed to a non-rotatable casing of a forward bearing of the air-breathing jet engine. 7. The air-breathing jet engine of claim 1, wherein the at least one electrical connection further comprises: a first electrode positioned on a leading edge of a fan blade of the air-breathing jet engine; anda second electrode positioned on a trailing edge of the fan blade, wherein the electrical resistive thermal material is positioned between the leading edge and the trailing edge. 8. The air-breathing jet engine of claim 7, wherein at least one of the first and second electrodes further comprises a conductive coating formed on the fan blade. 9. The air-breathing jet engine of claim 7, wherein at least one of the first and second electrodes further comprises a conductive coating formed at least partially within the fan blade. 10. The air-breathing jet engine of claim 7, wherein the at least one electrical connection further comprises at least one electrical cable positioned through the fan blade. 11. The air-breathing jet engine of claim 1, wherein the at least one electrical ground connection has at least one grounding cable positioned at least partially through a hollow center of the at least one rotatable shaft. 12. The air-breathing jet engine of claim 1, further comprising at least one of a temperature sensor and an ice detection sensor positioned on the air-breathing jet engine. 13. The air-breathing jet engine of claim 12, further comprising a control system interfaced with the at least one of a temperature sensor and ice detection sensor, wherein the control system controls a quantity of thermal energy produced by the electrical resistive thermal material. 14. The air-breathing jet engine of claim 13, further comprising an electrical switching system in communication with the control system, wherein the electrical switching system controls a distribution of a quantity of electrical power generated by the reversed PMEG to the electrical resistive thermal material. 15. The air-breathing jet engine of claim 1, wherein the portion of the air-breathing jet engine on which the electrical resistive thermal material is positioned further comprises at least one of: an engine spinner;a fan blade;a low-pressure compressor casing; anda low-pressure compressor. 16. The air-breathing jet engine of claim 1, wherein the reversed PMEG further comprises a stator having the at least one fixed magnet, wherein the at least one rotatable winding is positioned interior of the stator. 17. A method of deicing an air-breathing jet engine, the method comprising the steps of: creating a quantity of electrical power with a reversed permanent magnet electric generator (PMEG) driven by at least one rotatable shaft of an air-breathing jet engine, wherein the reversed PMEG has at least one fixed magnet and at least one rotatable winding;sensing a thermal condition of an externally exposed portion of a rotatable fan blade of the air-breathing jet engine; andsupplying the quantity of electrical power to an electrical resistive thermal material positioned on the externally exposed portion of the rotatable fan blade of the air-breathing jet engine, whereby a quantity of thermal energy is provided to the externally exposed portion of the rotatable fan blade. 18. The method of claim 17, wherein creating the quantity of electrical power with the reversed PMEG with the at least one rotatable shaft further comprises rotating the at least one rotatable winding connected to the at least one rotatable shaft past a stator having the at least one fixed magnet. 19. The method of claim 17, further comprising controlling supplying the quantity of electrical power to the electrical resistive thermal material with a control system, wherein the control system further comprises an ice detection sensor. 20. The method of claim 19, further comprising controlling a distribution of the quantity of electrical power generated by the reversed PMEG to the electrical resistive thermal material with an electrical switching system in communication with the control system. 21. A system for deicing a turbofan, the turbofan having at least one rotatable shaft connected to a plurality of fan blades, comprising: a reversed permanent magnet electric generator (PMEG) having a stator with at least one fixed magnet and at least one rotatable winding, wherein the at least one rotatable winding is mechanically connected to the at least one rotatable shaft, and wherein the stator is positioned between the at least one rotatable winding and the at least one rotatable shaft;at least one electrical ground connection having a grounding cable connected between the at least one rotatable winding and an aircraft airframe, wherein the grounding cable is positioned at least partially through a hollow center of the at least one rotatable shaft;an electrical resistive thermal material positioned on each of the plurality of fan blades; andat least one electrical connection between the reversed PMEG and the electrical resistive thermal material, wherein the at least one electrical connection has at least one electrode positioned on an edge of each of the plurality of fan blades.
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이 특허에 인용된 특허 (6)
Dooley Kevin A. (Georgetown CAX) Morris Elwood A. (Brampton CAX), Electrical anti-icer for a turbomachine.
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