Resistive-inductive propeller blade de-icing system including contactless power supply

Patent metadata

Field	Value
Publication number	US-9638044-B2
Application number	US-201414203813-A
Country	US
Kind code	B2
Filing date	Mar 11, 2014
Priority date	Mar 11, 2014
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

An aircraft propeller de-icing system comprises at least one propeller blade coupled to a rotatable prop assembly. The prop assembly is configured to rotate in response to rotatably driving a propeller shaft. At least one resistive-inductive heating unit is coupled to the at least one propeller blade. The resistive-inductive heating unit is configured to generate eddy currents that induce inductive heat in response to an electric current. A contactless power transfer system generates the electrical current in response to transferring power across an air gap separating the propeller shaft from the contactless power transfer system.

First claim

The invention claimed is:

1. An aircraft propeller de-icing system comprising:
at least one propeller blade coupled to a rotatable prop assembly, the prop assembly configured to rotate in response to rotatably driving a propeller shaft;
at least one resistive-inductive heating unit coupled to the at least one propeller blade, the resistive-inductive heating unit configured to generate eddy currents that induce inductive heat in response to an electric current; and
a contactless power transfer system that generates electrical current in response to transferring power across an air gap separating the propeller shaft from the contactless power transfer system,
wherein the contactless power transfer system includes a rotary transformer, the rotary transformer comprising:

a primary winding coupled to a stationary portion of the aircraft and configured to generate an electromagnetic field in response to an alternating excitation current;
a secondary winding separated from the primary winding via the air gap and configured to rotate about the primary winding; and
a power control module configured to generate alternating excitation current to the primary winding, the secondary winding generating the electrical current that is delivered to a plurality of electrically conductive resistive-inductive elements of the resistive-inductive heating unit in response to realizing the electromagnetic field.

2. The aircraft propeller de-icing system of claim 1 , wherein the contactless power transfer system further comprises at least one sensor that determines at least one environmental condition, and wherein the power control module generates the alternating excitation current in response to determining the at least one environmental condition.

3. The aircraft propeller de-icing system of claim 1 , wherein the plurality of electrically conductive resistive-inductive elements generates an electromagnetic field in response to the electrical current, the electromagnetic field inducing the eddy currents that generate the inductive heat.

4. The aircraft propeller de-icing system of claim 3 , wherein the plurality of electrically conductive resistive-inductive elements are formed on a flexible substrate and arranged in a matrix configuration.

5. The aircraft propeller de-icing system of claim 4 , wherein the resistive-inductive heating unit includes a pair of insulating elements, and wherein the plurality of electrically conductive resistive-inductive elements are interposed between the insulating elements; and
at least one current conducting element isolated from the plurality of resistive-inductive elements and disposed against one or more portions of a respective propeller blade,
wherein the eddy currents are generated in the at last one current conducting element to generate the inductive heat.

6. The aircraft propeller de-icing system of claim 5 , wherein the matrix configuration of the plurality of electrically conductive resistive-inductive elements includes an m x n matrix, wherein m resistive-inductive elements are connected in series and n resistive-inductive elements are connected in parallel.

7. The aircraft propeller de-icing system of claim 6 , wherein the plurality of electrically conductive resistive-inductive elements connected in series have an alternating magnetic polarity with respect to one another, the magnetic polarity intensifying the eddy currents flowing through the at last one current conducting element.

8. The aircraft propeller de-icing system of claim 7 , wherein the contactless power transfer system includes a wound field synchronous generator, the wound field synchronous generator comprising:
a field excitation winding coupled to a stationary portion of the aircraft and configured to generate an electromagnetic field in response to a direct current;
an armature winding separated from the field excitation winding via the air gap and configured to rotate about the field excitation winding; and
a power control module configured to generate the direct current to the a field excitation winding, the armature winding generating the electrical current that is delivered to the plurality of resistive-inductive elements in response to realizing the electromagnetic field.

9. The aircraft propeller de-icing system of claim 8 , wherein the armature winding includes a three-phase armature winding that generates an alternating current to the plurality of resistive-inductive elements.

10. The aircraft propeller de-icing system of claim 9 , wherein the contactless power transfer system further comprises at least one sensor that determines at least one environmental condition, and wherein the power control module generates the direct current in response to determining the at least one environment condition.

11. A resistive-inductive heating unit configured to de-ice at least one aircraft propeller blade, the resistive-inductive heating unit comprising:
a current conducting element disposed on the at least one propeller blade;
a first insulating element disposed on the current conducting element;
at least two pairs of resistive-inductive elements disposed on the first insulating element;
a second insulating element disposed on the at least two pairs of resistive-inductive elements, the at least two pairs of resistive-inductive elements interposed between the first and second insulating elements and electrically insulated from the current conducting element
wherein the at least two pairs of resistive-inductive elements generate an electromagnetic field in response to an electrical current, the electromagnetic field inducing eddy currents in the current conducting element to generate inductive heat that heats the at least one aircraft propeller blade,
wherein the contactless power transfer system includes a rotary transformer, the rotary transformer comprising:

a primary winding coupled to a stationary portion of the aircraft and configured to generate an electromagnetic field in response to an alternating excitation current;
a secondary winding separated from the primary winding via the air gap and configured to rotate about the primary winding; and
a power control module configured to generate alternating excitation current to the primary winding, the secondary winding generating the electrical current that is delivered to a that at least two pairs of resistive-inductive elements in response to realizing the electromagnetic field.

12. The resistive-inductive heating unit of claim 11 , wherein each pair of resistive-inductive heating elements is separated from one another by an air gap.

13. The resistive-inductive heating unit of claim 12 , wherein the current conducting element is formed from aluminum.

14. The resistive-inductive heating unit of claim 13 , wherein a first pair of resistive-inductive elements generates a first magnetic polarity and a second pair of resistive-inductive elements generates a second magnetic polarity that is opposite from the first magnetic polarity.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Gieras Jacek F
• Ribarov Lubomir A

Classifications

• H05B6/105

  using a susceptor · CPC title

• H05B2214/02

  Heaters specially designed for de-icing or protection against icing · CPC title

• H05B1/0236

  for vehicles · CPC title

• B64D15/12 Primary

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title

• F01D5/18 Primary

  Hollow blades, {i.e. blades with cooling or heating channels or cavities (structure of hollow blades in general F01D5/147)}; Heating, heat-insulating or cooling means on blades · CPC title