METHOD FOR FORMING AN IN SITU TEMPORARY BARRIER WITHIN A GAS TURBINE ENGINE

A method for forming an in situ temporary barrier within a gas turbine engine 10 is provided. The method can include installing a bladder 100 within the gas turbine engine 10, wherein the bladder 100 defines a bladder body 102, and inflating the bladder 100 with an inflating fluid such that the blad...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	ROBERTS, Herbert Chidsey, DIWINSKY, David Scott
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING COMBINED OPERATIONS ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS STEAM ENGINES TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	A method for forming an in situ temporary barrier within a gas turbine engine 10 is provided. The method can include installing a bladder 100 within the gas turbine engine 10, wherein the bladder 100 defines a bladder body 102, and inflating the bladder 100 with an inflating fluid such that the bladder body 102 forms a circumferential seal within the gas turbine engine 10. The bladder body 102 can be positioned between a row of stator vanes 70, 80 and an annular array of rotating blades 68, 82 to form a circumferential seal therebetween. A second bladder 200 may be positioned circumferentially within the gas turbine engine.