GAS TURBINE ENGINE WITH SPLIT HELICAL PISTON SEAL

A gas turbine engine (20) includes a rotor (62) that has a sealing surface (68) and a shaft (70) that is rotatable about an engine central axis (A). The shaft (70) has an annular seal channel (72) that opens to the seal surface (68), and there is a split seal (74) that is insertable into the annular...

Ausführliche Beschreibung

Gespeichert in:

Bibliographische Detailangaben
Hauptverfasser:	KLING, Colin J, LYDERS, David R
Format:	Patent
Sprache:	eng ; fre ; ger
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 PISTONS SEALINGS STEAM ENGINES THERMAL INSULATION IN GENERAL WEAPONS
Online-Zugang:	Volltext bestellen
Tags:	Tag hinzufügen Keine Tags, Fügen Sie den ersten Tag hinzu!

Beschreibung
Zusammenfassung:	A gas turbine engine (20) includes a rotor (62) that has a sealing surface (68) and a shaft (70) that is rotatable about an engine central axis (A). The shaft (70) has an annular seal channel (72) that opens to the seal surface (68), and there is a split seal (74) that is insertable into the annular seal channel (72) for sealing against the seal surface (68). The split seal (74) includes first and second end sections (74a, 74b) that are mateable to each other. The split seal (74) has a helical shape when in a state of rest such that the first and second end sections (74a, 74b) are axially offset from each other.