BLADE TIP CLEARANCE CONTROL OF AIRCRAFT GAS TURBINE ENGINE

PROBLEM TO BE SOLVED: To provide a method and a system for predicting an engine command that changes the rotation speed of an engine and adjusting, before the command, a blade tip clearance (CL) between rotary blade tips of an aircraft gas turbine engine and a surrounding shroud.SOLUTION: By expandi...

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Bibliographische Detailangaben
Hauptverfasser:	RUIZ RAFAEL JOSE, GARDNER DONALD LEE, HERSHEY JOHN ERIK, HERRON WILLIAM LEE, OSBORN BROCK ESTEL
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	PROBLEM TO BE SOLVED: To provide a method and a system for predicting an engine command that changes the rotation speed of an engine and adjusting, before the command, a blade tip clearance (CL) between rotary blade tips of an aircraft gas turbine engine and a surrounding shroud.SOLUTION: By expanding or shrinking the shroud 72 before the engine command, a step of deciding a time point for starting to adjust the tip clearance (CL) can be included. Data of an aircraft and/or aircraft crew can include communication between the aircraft crew and an air traffic controller or an air traffic control substitute device. The step of deciding the time point for starting to adjust the tip clearance (CL) can include a step of using a learning algorithm capable of using: the operation experience of the aircraft gas turbine engine; and/or the operation experience of the other jet engine of the aircraft including the aircraft gas turbine engine and/or the other aircraft.