Gasturbinendeckband

A gas turbine engine (10) having a main casing (242), turbine blades (230) and a segmented cylindrical liner (240) surrounding the tips of the blades (230) is provided with apparatus for compensating for different radial expansions between the blades (230) and the liner (240). The apparatus comprise...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	MAGGS, PETER JOHN, BATH BA3 4BP, GB, LEONARD, JOHN FREDERICK, BRISTOL BS17 2AB, GB
Format:	Patent
Sprache:	ger
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
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A gas turbine engine (10) having a main casing (242), turbine blades (230) and a segmented cylindrical liner (240) surrounding the tips of the blades (230) is provided with apparatus for compensating for different radial expansions between the blades (230) and the liner (240). The apparatus comprises a shroud structure (238), such as a platform (238) of an axially adjacent nozzle guide vane (234) and a slipper element (250) extending radially from the shroud structure (238) to the liner (240) and coupling one to the other. The slipper element (250) expands circumferentially more slowly than does the shroud structure (238). Thermal circumferential growth of the shroud structure (238) causes a radial displacement of the liner segments (24) relative to the shroud structure (238).