An intercomponent seal for a gas turbine engine

An annular wall for a gas turbine engine comprises a plurality of circumferential wall segments 312,314. Opposing faces 320,322 of adjacent wall segments 312,314 define an intersegment gap 316 and include a saddle portion 318 facing radially outwards which receives a longitudinal seal member 324. Th...

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Bibliographische Detailangaben
1. Verfasser:	Steven Hillier
Format:	Patent
Sprache:	eng
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CYLINDERS ENGINE PLANTS IN GENERAL ENGINEERING ELEMENTS AND UNITS GAS-TURBINE PLANTS GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVEFUNCTIONING OF MACHINES OR INSTALLATIONS 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 NON-POSITIVE DISPLACEMENT PUMPS PISTONS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS SEALINGS STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
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Beschreibung
Zusammenfassung:	An annular wall for a gas turbine engine comprises a plurality of circumferential wall segments 312,314. Opposing faces 320,322 of adjacent wall segments 312,314 define an intersegment gap 316 and include a saddle portion 318 facing radially outwards which receives a longitudinal seal member 324. The longitudinal seal member 324 has a curved sealing surface 328, which contacts at least one of the opposing faces 320,322, and it may be substantially cylindrical. At least one axial restraint feature is provided on the seal member which engages with a corresponding feature of the wall segment or a wall segment support structure. Preferably, the axial restraint features are projecting flanges (512c, fig 5c) or slots (520d, fig 5d) engaged with support structure plates (516c/d, fig 5c/d) to restrict axial movement of the seal member in a downstream direction.