CORE DUCT ASSEMBLY FOR A GAS TURBINE ENGINE

The present invention relates to a core duct assembly (43) for a gas turbine engine (10), the assembly comprising: a core duct (44) with an outer wall (48) having an interior surface (52) and an inner wall (46), a vane (54) extending between said inner and outer walls and at least one rotor blade (5...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	Bousfield, Ian, MacDougall, Duncan
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	The present invention relates to a core duct assembly (43) for a gas turbine engine (10), the assembly comprising: a core duct (44) with an outer wall (48) having an interior surface (52) and an inner wall (46), a vane (54) extending between said inner and outer walls and at least one rotor blade (56) located downstream of the vane, the rotor blade extending between a platform (56c) and a tip (56d). An upstream wall axis (102) is defined as an axis tangential to a point on a first portion (62) of the interior surface (52) of the outer wall (52) of the core duct (44) extending downstream from the vane (54) and wherein the upstream wall axis intersects the rotor blade (56) at a point spaced radially inward by a distance (c) from the rotor blade tip (56d). Thus, rotor damages due to shed ice are mitigated.