Gap filler for a fuel system gallery

A nozzle assembly for a gas turbine engine, comprising: a nozzle at a downstream end of the assembly relative to fuel flow; a first and a second body upstream of the nozzle, the first body defining a first passage between a first inlet connectable to a source and a first outlet, and the second body...

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Bibliographische Detailangaben
Hauptverfasser:	Swaby, Nadia, Sreekanth, Sri
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION APPARATUS COMBUSTION ENGINES COMBUSTION PROCESSES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS GAS-TURBINE PLANTS GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGHVELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	A nozzle assembly for a gas turbine engine, comprising: a nozzle at a downstream end of the assembly relative to fuel flow; a first and a second body upstream of the nozzle, the first body defining a first passage between a first inlet connectable to a source and a first outlet, and the second body defining a second passage between a second inlet and a second outlet in fluid communication with the nozzle, the inlets in fluid communication with each other; the bodies matingly engaged together along an axis, the inlets spaced apart relative to the axis to define a gallery having a depth in an axial direction and a width in a transverse direction; and a gap filler within the gallery, compressible in at least one of the directions, having an uncompressed dimension greater than a corresponding dimension of the gallery in the at least one of the directions.