Fluid pressure based icing detection for a turbine engine

An icing detection subsystem 200 for an aircraft turbine engine 202 is presented. The icing detection subsystem includes a plurality of air pressure sampling ports 204 formed within structure that surrounds a rotating component of the aircraft turbine engine. The subsystem also includes a pressure s...

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Bibliographische Detailangaben
Hauptverfasser:	GOODWIN, RONALD, REPP, JOHN, DISCHINGER, DAVE, HANSON, DAVID RICHARD
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COSMONAUTICS ENGINE PLANTS IN GENERAL EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PARACHUTES PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	An icing detection subsystem 200 for an aircraft turbine engine 202 is presented. The icing detection subsystem includes a plurality of air pressure sampling ports 204 formed within structure that surrounds a rotating component of the aircraft turbine engine. The subsystem also includes a pressure sensor arrangement 206 coupled to the plurality of air pressure sampling ports to obtain air pressure measurements for the plurality of air pressure sampling ports. A processing module 208 is coupled to the pressure sensor arrangement to analyze the air pressure measurements over time during operation of the aircraft turbine engine, and to generate an alert 210 when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice in the aircraft turbine engine.