US 12,110,825 B1
Systems and method for detecting and responding to icing conditions in gas turbine engines
Stefan Cafaro, Chapel Hill, NC (US); Brendon Leeker, Cincinnati, OH (US); Kevin Graziano, Liberty Township, OH (US); and Kum-Kang Huh, Niskayuna, NY (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Aug. 29, 2023, as Appl. No. 18/239,459.
Int. Cl. F02C 7/047 (2006.01); F02C 9/50 (2006.01)
CPC F02C 7/047 (2013.01) [F02C 9/50 (2013.01); F05D 2220/323 (2013.01); F05D 2270/053 (2013.01); F05D 2270/09 (2013.01); F05D 2270/335 (2013.01)] 13 Claims
OG exemplary drawing
 
3. An engine controller comprising:
a feedback interface electrically coupled to one or more electric machine motor generators deployed in an aircraft engine;
a processor electrically coupled to the feedback interface;
a memory electrically coupled to the processor;
wherein the memory is configured to store reference data indicative of a presence of an icing condition;
wherein the processor is configured to monitor a feedback signal received at the feedback interface from the one or more electric machine motor generators and identify the icing condition as present based on a combination of the feedback signal and the reference data;
wherein the engine controller further comprises a control interface electrically coupled to the processor and configured to electrically couple to one or more components of the aircraft engine, wherein the processor is configured to direct, via the control interface, the one or more components to alter a current operating condition of the aircraft engine in response to the processor determining that the icing condition is present; and
wherein the current operating condition includes a pitch of one or more fans and a speed of one or more cores of the aircraft engine that the processor is configured to alter while maintaining a current thrust output of the aircraft in response to the processor determining that the icing condition is present.