FLUID PRESSURE BASED ICING DETECTION FOR A TURBINE ENGINE

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

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Bibliographische Detailangaben
Hauptverfasser:	HANSON DAVID RICHARD, DISCHINGER DAVE, REPP JOHN, GOODWIN RONALD
Format:	Patent
Sprache:	eng
Schlagworte:	ALARM SYSTEMS BLASTING COMBUSTION ENGINES ENGINE PLANTS IN GENERAL HEATING HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINEPLANTS HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NOT OTHERWISE PROVIDED FOR ORDER TELEGRAPHS PHYSICS SIGNALLING SIGNALLING OR CALLING SYSTEMS STEAM ENGINES USE OF WASTE HEAT OF COMBUSTION ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	An icing detection subsystem for an aircraft turbine engine is presented. The icing detection subsystem includes a plurality of air pressure sampling ports formed within structure that surrounds a rotating component of the aircraft turbine engine. The subsystem also includes a pressure sensor arrangement 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 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 when at least one characteristic of the air pressure measurements over time is indicative of the presence of ice in the aircraft turbine engine.