US 11,946,421 B2
Use of particulate sensor in engine power assurance
Jacques Paul, Lynn, MA (US); Charles W. Dowdell, Lynn, MA (US); and James R. Noel, Lynn, MA (US)
Assigned to General Electric Company, Schenectady, NY (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Feb. 10, 2022, as Appl. No. 17/669,335.
Prior Publication US 2023/0250762 A1, Aug. 10, 2023
Int. Cl. F02C 9/00 (2006.01); F02C 7/04 (2006.01)
CPC F02C 9/00 (2013.01) [F02C 7/04 (2013.01); F05D 2260/80 (2013.01)] 20 Claims
OG exemplary drawing
 
13. A system, comprising:
a controller of an aircraft engine, the controller comprising a processor and a memory; and
a plurality of sensors electrically coupled to the aircraft engine, comprising:
(i) a particulate sensor configured to measure at least one of (a) particulate matter in a gas path of the aircraft engine or (b) accumulated particulate matter in the aircraft engine;
(ii) a second sensor configured to detect an operational state of the aircraft engine; and
(iii) a third sensor configured to detect an environmental state of the aircraft engine;
wherein:
the memory is configured to store an aircraft engine power model for simulating an operational state of the aircraft engine as a function of the environmental state of the aircraft engine;
the processor is configured to determine an efficiency of the aircraft engine based on (i) the aircraft engine power model, and (ii) particulate sensor data pertaining to particulate matter in a gas flow, second sensor data of the operational state of the aircraft engine, and third sensor data of the environmental state of the aircraft engine; and
the processor is further configured to extrapolate from the efficiency a maximum power of the aircraft engine under flight conditions.