US 11,873,098 B2
Heater design for carbon allotrope ice protection systems
Casey Slane, Tallmadge, OH (US); Jin Hu, Hudson, OH (US); Nathaniel Ching, Hartville, OH (US); Galdemir Cezar Botura, Akron, OH (US); James A. Mullen, Wadsworth, OH (US); and Mark James Didyk, Mogadore, OH (US)
Assigned to GOODRICH CORPORATION, Charlotte, NC (US)
Filed by Goodrich Corporation, Charlotte, NC (US)
Filed on Sep. 17, 2019, as Appl. No. 16/573,123.
Claims priority of provisional application 62/748,975, filed on Oct. 22, 2018.
Prior Publication US 2020/0140097 A1, May 7, 2020
Int. Cl. B64D 15/12 (2006.01); H05B 3/14 (2006.01); B82Y 30/00 (2011.01); F02C 7/047 (2006.01)
CPC B64D 15/12 (2013.01) [H05B 3/145 (2013.01); B82Y 30/00 (2013.01); F02C 7/047 (2013.01); H05B 2203/017 (2013.01); H05B 2214/02 (2013.01); H05B 2214/04 (2013.01)] 10 Claims
OG exemplary drawing
 
1. An ice protection system for an aircraft component comprising:
a first section of the aircraft component having a first span and a first chord;
a second section of the aircraft component, adjacent to the first section of the aircraft component, having a second span and a second chord, wherein the first section of the aircraft component and the second section of the aircraft component meet at a joint;
a junction section comprising:
an end portion of the first section of the aircraft component;
an end portion of the second section of the aircraft component adjacent to the end portion of the first section of the aircraft component, and
the joint;
a first plurality of heaters expanding spanwise across the first section of the aircraft component configured to heat the first section of the aircraft component;
a second plurality of heaters expanding spanwise across the second section of the aircraft component configured to heat the second section of the aircraft component;
a first H-shaped heater on the first section of the aircraft component expanding into the junction section, wherein the first H-shaped heater has at least one chordwise section connected to at least one spanwise section and the at least one chordwise section is positioned in the junction section close to the joint such that the at least one chordwise section is configured to heat the end portion of the first section of the aircraft component; and
a second H-shaped heater on the second section of the aircraft component, expanding into the junction section, wherein the second H-shaped heater has at least one chordwise section connected to at least one spanwise section and the at least one chordwise section is positioned in the junction section close to the joint such that the at least one chordwise section is configured to heat the end portion of the second section of the aircraft component.