US 12,228,039 B2
Aircraft engine sensing apparatus with insulated connection wires
Joel Douglas Stolfus, Freeport, IL (US)
Assigned to Honeywell International Inc., Charlotte, NC (US)
Filed by Honeywell International Inc., Charlotte, NC (US)
Filed on Feb. 2, 2024, as Appl. No. 18/431,882.
Application 18/431,882 is a continuation of application No. 17/808,286, filed on Jun. 22, 2022, granted, now 11,927,104.
Prior Publication US 2024/0218806 A1, Jul. 4, 2024
Int. Cl. F01D 21/00 (2006.01); B64D 45/00 (2006.01); G01P 1/02 (2006.01)
CPC F01D 21/003 (2013.01) [B64D 45/00 (2013.01); G01P 1/026 (2013.01)] 16 Claims
OG exemplary drawing
 
1. A method of manufacturing an aircraft engine sensing apparatus, the method comprising:
providing an aircraft engine sensor and a sensor connector;
welding a first end of a wire protection housing to a sensor protection housing, wherein a plurality of connection wires is positioned within the wire protection housing, the plurality of connection wires connecting the aircraft engine sensor to the sensor connector;
positioning at least one ceramic insulator within the wire protection housing such that an outer surface of the at least one ceramic insulator is in contact with an inner surface of the wire protection housing, the at least one ceramic insulator defining a plurality of insulator openings, wherein each of the plurality of connection wires passes through a corresponding one of the plurality of insulator openings, wherein the at least one ceramic insulator is positioned between the aircraft engine sensor and the sensor connector, and wherein at least a portion of the first end of the wire protection housing is not insulated by the at least one ceramic insulator; and
injecting glass insulators into the portion of the first end of the wire protection housing not insulated by the at least one ceramic insulator, wherein the glass insulators provide an insulation layer within the wire protection housing and between the sensor protection housing and the at least one ceramic insulator.